Sum m ary 
Report on 
B AASS U AP 
Analysis 
C apabilities
N ovem ber 23, 2010


Sum m ary 
Report on 
B AASS U AP 
Analysis 
C apabilities
N ovem ber 23, 2010


TABLE OF CONTENTS
Pg-
LIST OF FIG URES............................................................................................................................4
LIST OF TAB LES..............................................................................................................................9
1. EXEC U TIVE SU M M ARY..........................................................................................................10
2. IN TRODU C TION.........................................................................................................................13
2.1 HISTORIC AL EVEN TS AN D STU DIES..........................................................................13
2.2 B AASS’ TW ELVE TEC HN OLOG Y FOC US AREAS....................................................14
2.3 B AASS PERSON N EL, SOFTW ARE, EQU IPM EN T AN D DATA 
W AREHOU SE.............................................................................................................15
2.3.1 B AASS Personnel........................................................................................................15
2.3.2 AN SYS M ultiphysics FEA..........................................................................................16
2.3.3 Equipm ent.....................................................................................................................16
2.3.4 DataW arehouse............................................................................................................19
3. TYPES OF U APS OB SERVED.................................................................................................21
4. AN ALYTIC AL AN D N U M ERIC AL SOLU TION S FOR U AP IN VESTIG ATION S...........25
4.1 "TIC  TAC " IN C IDEN T........................................................................................................25
4.1.1 Analytical Solutions of Velocities and Accelerations Associated with
" Tic Tac" Perform ance......................................................................................  32
4.1.2 Sum m ary of Analytical Velocity and Acceleration Solutions...................................32
4.1.3 N um erical Analysis of C om pressible Flow...............................................................39
4.1.4 Sum m ary and C onclusions of C om pressible N um erical Analyses...........................46
4.1.5 N um erical Analysis of Incom pressible Flow of a U AP Entering W ater..................47
4.1.6 N um erical Analysis of Incom pressible Flow of a U AP Entering W ater 
Results............................... 48
4.1.7 Sum m ary and C onclusions of N um erical Analysis of Incom pressible Flow 
of a U AP Entering W ater Results...................    58
4.2 AN ALYSES OF SPHERIC AL U APS.................................................................................58
4.2.1 Acoustical Analysis of a Spherical U SO....................................................................58
4.2.2 AN SYS M ultiphysics Electrom agnetic C apabilities..............................  82
4.2.3 Radar C ross Section Analysis of a Spherical U FO....................................................83
5. SU M M ARY AN D C ON C LU SION ............................................................................................98
6. REFEREN C ES............................................................................................................................100
SYM B OLS AN D AC RON YM S....................................................................................................102
AT TAC HM EN T I - AN SYS IN PU T FILES.............................................................................105
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U SO AN SYS M ultiphysics Acoustics Input File Exam ple.......................................................105
U AP AN SYS M ultiphysics RC S Input File Exam ple.............................................................112
ATTAC HM EN T II - "TIC  TAC " C FD C ON TOU R PLOTS FOR PRESSU RE, 
TEM PERATU RE AN D M AC H N U M B ER.................................................................................116
ATTAC HM EN T III - RIG HT C IRC U LAR C YLIN DER C FD C ON TOU R PLOTS 
FOR PRESSU RE, TEM PERATU RE AN D M AC H N UM B ER..................................................128
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LIST OF FIGURES
P&
Figure 1. The U FO Pattern: A C ondensed Statem ent of Repealed Observations.........................21
Figure 2. Lockheed M artin Skunk W orks SR-71 B lack B ird.........................................................22
Figure 3. Lockheed F-l 17 N ighthawk Stealth Fighter...................................................................22
Figure 4. N orthrop G rum m an B -2 Spirit Stealth B om ber..............................................................23
Figure 5. B oeing Phantom  W orks B -2 Stealth X-45A U AV..........................................................23
Figure 6. Three Dim ensional Rendering of a C ylindrical or “Tic Tac” U AP...............................24
Figure 7. Three Dim ensional Rendering of a M etallic Spherical U AP.........................................24
Figure 8. Location of the AAV during the F/A18 Intercept...........................................................26
Figure 9. FLIR in 'W hite Hot’ M ode................................................................................................30
Figure 10. FLIR in "B lack Hot" m ode............................................................................................30
Figure 11. Tic Tac Param etric Velocities for Selected Tim es of Event Duration 
in ft/sec.........................................................................................................35
Figure 12. Tic Tac Param etric Velocities for Selected Tim es of Event Duration 
in m ph......................  36
Figure 13. Tic Tac Param etric Accelerations for Selected Tim es of Event Duration 
in ft/sec2........................................................................    37
Figure 14. Tic Tac Param etric Accelerations for Selected Tim es of Event Duration 
in g...............................................................................................................38
Figure 15. Tic Tac Pressure at 1/6 Scale, Air Tem perature 223K  and 700 m ph 
with M ixed Inlet and Supersonic Outlet.........................  41
Figure 16. Tic Tac Tem perature at 1/6 Scale, Air Tem perature 223K  and 700 m ph 
with M ixed Inlet and Supersonic Outlet.....................................................41
Figure 17. Tic Tac M ach N um ber at I /6 Scale, Air Tem perature 223K  and 700 m ph 
with M ixed Inlet and Supersonic Outlet.....................................................42
Figure 18. Tic Tac Pressure at 1/6 Scale, Air Tem perature 223K  and 1500 m ph 
with Supersonic Inlet and Supersonic Outlet..............................................42
Figure 19. Tic Tac Tem perature al 1/6 Scale, Air ‘Tem perature 223K  and 1500 m ph 
with Supersonic Inlet and Supersonic Outlet..............................................43
Figure 20. Tic Tac M ach N um ber at I /6 Scale, Air Tem perature 223K  and 1500 m ph 
with Supersonic Inlet and Supersonic Outlet.............................................43
Figure 21. C ylinder Tem perature at 1/6 Scale, Air Tem perature 223K  and 700 m ph 
with M ixed Inlet and Supersonic Outlet.....................................................44
Figure 22. C ylinder M ach N um ber at 1/6 Scale, Air Tem perature 223 K  and 700 m ph 
with M ixed Inlet and Supersonic Outlet.....................................................44
Figure 23. C ylinder Pressure al 1/6 Scale, Air Tem perature 223K  and 1500 m ph 
with Supersonic Inlet and Supersonic Outlet..............................................45
Figure 24. C ylinder Tem perature at 1/6 Scale, Air Tem perature 223K  and 1500 m ph 
with Supersonic Inlet and Supersonic Outlet......................  45
Figure 25. C ylinder M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 1500 m ph 
with Supersonic Inlet and Supersonic Outlet......................................  46
Figure 26. Solid Three Dim ensional G eom etry of Disc and W ater................................................50
Figure 27. Solid Three Dim ensional G eom etry M esh of Disc and W ater......................................51
Figure 28. Solid Three Dim ensional G eom etry M esh of U AP Disc..............................................52
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Figure 29. U ser G enerated C ut Analysis Plane...............................................................................53
Figure 30, Anim ated Result, Fluid 2 Volum e Fraction..................................................................54
Figure 31, Total Pressure Around U AP.......................  55
Figure 32. W ater Surface Effects From  Solid Im pact...................................................................56
Figure 33. W ater Surface Effects From  Solid Im pact (Side View)..........................................  57
Figure 34. M esh Plot for 1,000 Hz with 25 Elem ents per W avelength in W ater.........................61
Figure 35. M esh Plot for 1,000 Hz with 50 Elem ents per W avelength in W ater.........................62
Figure 36. C ontour Plot of Real C om ponent of Pressure (Pa) for 1,000 Hz 
with 50 Elem ents per W avelength in W ater...............................................63
Figure 37. C ontour Plot of Real C om ponent of Pressure (Pa) for 1,000 Hz 
with 50 Elem ents per W avelength in W ater..............................................64
Figure 38. C ontour Plot of Im aginary C om ponent of Pressure (Pa) for 1,000 Hz 
with 25 Elem ents per W avelength in W ater...............................................65
Figure 39. C ontour Plot of the M agnitude of Pressure (Pa) for 1,000 Hz 
with 25 Elem ents per W avelength in W ater...............................................66
Figure 40. Steady State Real C om ponent of Pressure (Pa) as a Function of Radial
Distance (m ) Plot for 1,000 Hz with 25 Elem ents per W avelength in W ater............67
Figure 41. Steady Slate Im aginary C om ponent of Pressure (Pa) as a Function 
of Radial Distance (m ) Plot for 1,000 Hz with 25 Elem ents per W avelength 
in W ater.........................................................................................................68
Figure 42. Steady State M agnitude of Pressure (Pa) as a Function of Radial
Distance (m ) Plot for 1,000 Hz. with 25 Elem ents per W avelength in W ater............69
Figure 43. C ontour Plot of Real C om ponent of Pressure (Pa) for 5,000 Hz 
with 25 Elem ents per W avelength in W ater...............................................70
Figure 44. C ontour Plot of Im aginary C om ponent of Pressure (Pa) for 5,000 Hz 
with 25 Elem ents per W avelength in W ater...............................................71
Figure 45. C ontour Plot of the M agnitude of Pressure (Pa) for 5,000 Hz 
with 25 Elem ents per W avelength in W ater...............................................72
Figure 46. Steady State Real C om ponent of Pressure (Pa) as a Function
of Radial Distance (m ) Plot for 5,000 Hz with 25 Elem ents per W avelength 
in W ater...........................................................................................................................73
Figure 47. Steady Stale Im aginary C om ponent of Pressure (Pa) as a Function
of Radial Distance (m ) Plot for 5,000 Hz with 25 Elem ents per W avelength 
in W ater...........................................................................................................................74
Figure 48. Steady Slate M agnitude of Pressure (Pa) as a Function of Radial
Distance (m ) Plot for 5,000 Hz with 25 Elem ents per W avelength in W ater............75
Figure 49. C ontour Plot of Real C om ponent of Pressure (Pa) for 10,000 1 Iz 
with 25 Elem ents per W avelength in W ater...............................................76
Figure 50. C onlour Plot of Im aginary C om ponent of Pressure (Pa) for 10,000 I Iz 
with 25 Elem ents per W avelength in W ater...............................................77
Figure 51. C ontour Plot of the M agnitude of Pressure (Pa) for 10,000 1 Iz 
with 25 Elem ents per W avelength in W ater...............................................78
Figure 52. Steady State Real C om ponent of Pressure (Pa) as a Function
of Radial Distance (m ) Plot for 10,000 Hz with 25 Elem ents per W avelength 
in W ater...........................................................................................................................79
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Figure 53. Steady State Im aginary C om ponent of Pressure (Pa) as a Function
of Radial Distance (m ) Plot for 10,000 Hz with 25 Elem ents per W avelength
in W ater............................................................................................................................80
Figure 54. Steady State M agnitude of Pressure (Pa) as a Function of Radial Distance (m )
Plot for 10,000 Hz with 25 Elem ents per W avelength in W ater..................................81
Figure 55. Factors that Determ ine the Energy Returned by a Target............................................83
Figure 56. Effect of Distance from  the radar to the Target on the Power Density.......................84
Figure 57. Reduction in the Strength of Target Echoes with Range.............................................87
Figure 58. G eom etry, Description and M axim um  RC S...............................................................88
Figure 59. Radar C ross Section C om parison.................................................................................89
Figure 60. M esh of 14 Sym m etry U FO Sphere with 25 Elem ents per W avelength.....................90
Figure 61. M esh of 14 Sym m etry U FO Sphere with 50 Elem ents per W avelength.....................91
Figure 62. N orm alized radar C ross Section Plot for a 14 Sym m etry 10 m  M etallic
Sphere with a 1 m  Dielectric C oating in Decibels for 300 M Hz and 25
Elem ents per W avelength...............................................................................................93
Figure 63. N orm alized radar C ross Section Plot for a 14 Sym m etry 10 m  M etallic
Sphere with a 1 m  Dielectric C oating in Decibels for 300 M Hz and
50 Elem ents per W avelength.........................................................................................95
Figure 64. Electric Filed C ontour in V/m  for a 14 Sym m etry 10 m  M etallic Sphere
with a I m  Dielectric C oating in Decibels for 300 M Hz and 25 Elem ents 
per W avelength............................................................................................................96
Figure 65. fie Tac Pressure at 1/6 Scale, Air Tem perature 223K  and 100 m ph 
with Subsonic Inlet and Subsonic Outlet.................................................116
Figure 66. Tic Tac Tem perature at 1/6 Scale, Air Tem perature 223K  and 100 m ph 
with Subsonic Inlet and Subsonic Outlet.................................................116
Figure 67. Tic Tac M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 100 m ph
with Subsonic Inlet and Subsonic Outlet....................................................................117
Figure 68. fie Tac Pressure at 1/6 Scale, Air Tem perature 223K  and 200 m ph 
with Subsonic Inlet and Subsonic Outlet.................................................117
Figure 69. Tic Tac Tem perature at 1/6 Scale, Air Tem perature 223K  and 200 m ph 
with Subsonic Inlet and Subsonic Outlet.................................................118
Figure 70. Tic Tac M ach N um ber at I /6 Scale, Air Tem perature 223K  and 200 m ph 
with Subsonic Inlet and Subsonic Outlet.................................................118
Figure 71. Tic Tac Pressure at 1/6 Scale, Air Tem perature 223K  and 300 m ph 
with Subsonic Inlet and Subsonic Outlet.................................................119
Figure 72. 1 ic Tac Tem perature at 1/6 Scale, Air Tem perature 223K  and 300 m ph
with Subsonic Inlet and Subsonic Outlet....................................................................119
Figure 73. Tic Tac M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 300 m ph
with Subsonic Inlet and Subsonic Outlet.....................................................................120
Figure 74. Tic Tac Pressure at 1/6 Scale, Air Tem perature 223K  and 400 m ph 
with M ixed Inlet and Subsonic Outlet.....................................................120
Figure 75. l ie Tac Tem perature at 1/6 Scale, Air Tem perature 223K  and 400 m ph 
with M ixed Inlet and Subsonic Outlet.......................................................121
Figure 76. Tic Tac M ach N um ber at 1/6 Scale, Air Tem perature 223 K  and 400 m ph
with M ixed Inlet and Subsonic Outlet.........................................................................121
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Figure 77. Tic Tac Pressure at 1/6 Scale, Air Tem perature 223K  and 500 m ph 
with M ixed Inlet and Subsonic Outlet.......................................................122
Figure 78. Tic Tac Tem perature at 1/6 Scale, Air Tem perature 223K  and 500 m ph 
with M ixed Inlet and Subsonic Outlet.......................................................122
Figure 79. Tic Tac M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 500 m ph 
with M ixed Inlet and Subsonic Outlet.......................................................123
Figure 80. Tic Tac Pressure at 1/6 Scale, Air Tem perature 223K  and 900 m ph 
with Supersonic Inlet and Supersonic Outlet............................................123
Figure 81. Tic Tac Tem perature at 1/6 Scale, Air Tem perature 223K  and 900 m ph 
with Supersonic Inlet and Supersonic Outlet............................................124
Figure 82. Tic Tac M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 900 m ph 
with Supersonic Inlet and Supersonic Outlet............................................124
Figure 83. Tic Tac Pressure at 1/6 Scale, Air Tem perature 223K  and 1100 m ph 
with Supersonic Inlet and Supersonic Outlet............................................125
Figure 84. Tic Tac Tem perature at 1/6 Scale, Air Tem perature 223K  and 1100 m ph 
with Supersonic Inlet and Supersonic Outlet............................................125
Figure 85. Tic Tac M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 1100 m ph 
with Supersonic Inlet and Supersonic Outlet............................................126
Figure 86. Tic Tac Pressure at 1/6 Scale, Air Tem perature 223K  and 1300 m ph 
with Supersonic Inlet and Supersonic Outlet............................................126
Figure 87. Tic Tac Tem perature at 1/6 Scale, Air Tem perature 223K  and 1300 m ph 
with Supersonic Inlet and Supersonic Outlet............................................127
Figure 88. Tic Tac M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 1300 m ph 
with Supersonic Inlet and Supersonic Outlet............................................127
Figure 89. C ylinder Pressure at 1/6 Scale, Air Tem perature 223K  and 100 m ph 
with Subsonic Inlet and Subsonic Outlet...................................................128
Figure 90. C ylinder Tem perature at 1/6 Scale, Air Tem perature 223K  and 100 m ph 
with Subsonic Inlet and Subsonic Outlet..................................................128
Figure 91. C ylinder M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 100 m ph 
with Subsonic Inlet and Subsonic Outlet..................................................129
Figure 92. C ylinder Pressure at 1/6 Scale, Air Tem perature 223K  and 200 m ph 
with Subsonic Inlet and Subsonic Outlet...................................................129
Figure 93. C ylinder Tem perature at 1/6 Scale, Air Tem perature 223K  and 200 m ph 
with Subsonic Inlet and Subsonic Outlet...................................................130
Figure 94. C ylinder M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 200 m ph 
with Subsonic Inlet and Subsonic Outlet.................................................130
Figure 95. C ylinder Pressure at 1/6 Scale, Air Tem perature 223K  and 300 m ph 
with Subsonic Inlet and Subsonic Outlet..................................................131
Figure 96. C ylinder Tem perature at 1/6 Scale, Air Tem perature 223K  and 300 m ph 
with Subsonic Inlet and Subsonic Outlet...................................................131
Figure 97. C ylinder M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 300 m ph 
with Subsonic Inlet and Subsonic Outlet...................................................132
Figure 98. C ylinder Pressure at 1/6 Scale, Air Tem perature 223K  and 400 m ph 
with Subsonic Inlet and Subsonic Outlet.................................................132
Figure 99. C ylinder Tem perature at 1/6 Scale, Air Tem perature 223K  and 400 m ph 
with Subsonic Inlet and Subsonic Outlet...................................................133
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Figure 100. C ylinder M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 400 m ph 
with Subsonic Inlet and Subsonic Outlet............................................133
Figure 101. C ylinder Pressure at 1/6 Scale, Air Tem perature 223K  and 500 m ph 
with M ixed Inlet and Subsonic Outlet................................................134
Figure 102. C ylinder Tem perature at 1/6 Scale, Air Tem perature 223 K  and 500 m ph 
with M ixed Inlet and Subsonic Outlet................................................134
Figure 103. C ylinder M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 500 m ph 
with M ixed Inlet and Subsonic Outlet................................................135
Figure 104. C ylinder Pressure at 1/6 Scale, Air Tem perature 223K  and 700 m ph 
with M ixed Inlet and Supersonic Outlet.............................................135
Figure 105. C ylinder Pressure at 1/6 Scale, Air Tem perature 223K  and 900 m ph 
with Supersonic Inlet and Supersonic Outlet......................................136
Figure 106. C ylinder Tem perature at 1/6 Scale, Air Tem perature 223K  and 900 m ph 
with Supersonic Inlet and Supersonic Outlet......................................136
Figure 107. C ylinder M ach N um ber at 1/6 Scale, Air 1'em perature 223K  and 900 m ph 
with Supersonic Inlet and Supersonic Outlet......................................137
Figure 108. C ylinder Pressure at 1/6 Scale, Air Tem perature 223K  and 1100 m ph 
with Supersonic Inlet and Supersonic Outlet......................................137
Figure 109. C ylinder Tem perature at 1/6 Scale, Air Tem perature 223K  and 1100 m ph 
with Supersonic Inlet and Supersonic Outlet......................................138
Figure 110. C ylinder M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 1100 m ph 
with Supersonic Inlet and Supersonic Outlet......................................138
Figure 111. C ylinder Pressure at 1/6 Scale, Air Tem perature 223K  and 1300 m ph 
with Supersonic Inlet and Supersonic Outlet......................................139
Figure 112. C ylinder Tem perature at 1/6 Scale, Air Tem perature 223K  and 1300 m ph 
with Supersonic Inlet and Supersonic Outlet......................................139
Figure 113. C ylinder M ach N um ber at 1/6 Scale, Air Tem perature 223K  and 1300 m ph 
with Supersonic Inlet and Supersonic Outlet......................................140
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LIST OF TABLES
Pg-
Table 1. M ach Regim es.....................................................................................................................32
Table 2. Velocities and Accelerations of Tic Tac for Param etric Tim e Durations of Event.......34
Table 3. Properties of W ater U sed for AN SYS Harm onic Analyses............................................60
Table 4. N orm alized radar C ross Section for a 10 m  M etallic Sphere with a 1 m
Dielectric C oating in Decibels for 300 M Hz and 25 Elem ents per W avelength...........92
Table 5. N orm alized radar C ross Section for a 10 m  M etallic Sphere with a 1 m
Dielectric C oating in Decibels for 300 M Hz and 50 Elem ents per W avelength...........94
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1. EXECUTIVE SUMMARY
The purpose of this report is to sum m arize the field data collection, in-house databases and 
com putational capabilities that currently reside at B igelow Aerospace Advanced Space Studies 
(B AASS) for the study of advanced aerospace technology. B etween 2008 and 2010 B AASS was 
contracted by the Defense W arning Office of the Defense Intelligence Agency (DIA) to create, 
staff, and equip a new organization in order to exam ine and analyze the threat to national 
security associated with advanced aerospace technology. B y selecting and m odeling a few 
sentinel cases of encounters with advanced aerospace technology, this report dem onstrates the 
in-house data collection, data storage and analysis resources built by B AASS under DIA 
contract IIIIM 402-08-C -0072.
Throughout the m illennia individuals have observed and reported unexplained phenom ena in the 
sky. Som e of these reports included bright and Hashing lights, objects streaking across the sky or 
silently hovering, and m ultiple colored and flashing structures m orphing into one. C ylindrical, 
cigar, spherical, lenticular, triangular and ellipsoid shaped structures have been reported hovering 
and/or accelerating at rapid rates from a stationary position. Som e of these abrupt, high speed 
m aneuvers have been harder to explain with conventional physics, considering the inherently 
poor aerodynam ic properties of m any of these objects. It should be stressed m any, but not all, of 
these sightings m ay be explained by natural phenom ena, or by unacknowledged aerospace 
technology.
Several official governm ent studies were conducted from the late 1940s until around 1970, but 
m any of these studies were superficial and lacking in rigor. Since 1970, because of an absence 
of research funding, the study of U nidentified Aerial Phenom ena (U AP) has been characterized 
by cursory analysis and am ateur, unscientific data collection.
Pilots, both civilian and m ilitary, have reported seeing unusual objects in the air, som e of which 
have been independently confirm ed by radar. During the 1960s and 1970s a series of incidents 
was reported along the so called N orthern Tier of the U nited States where silent hovering objects 
were observed over m ilitary facilities housing nuclear weapons. One report in M arch 1967 
involving the sim ultaneous disabling of m ultiple m issiles for a period of tim e, while a U AP 
allegedly hovered nearby, stim ulated considerable public interest when inform ation of the event 
began to em erge. The 1967 incident, if true, as well as other N orthern Tier incidents, arguably 
had national security im plications.
Over the years, there have also been num erous reports of U nidentified Subm erged Objects 
(U SO), in all bodies of water. Som e U SO and U AP reportedly exhibited superior perform ance 
capabilities in velocity and acceleration underwater in the absence of detectable turbulence or 
cavitation signatures. W hile com paring our state of the art m ilitary equipm ent with these 
capabilities a reasonable individual m ay conclude there are national security im plications.
B igelow Aerospace Advanced Space Studies, I.LC  (B AASS) is a research organization focused 
on the identification, evaluation, and acquisition of novel and em erging future technologies 
worldwide as they specifically relate to air and space craft. C utting edge research areas include 
propulsion system s, space applications of nanosensors, piezoelectric and nanowire fabrics, 
hum an perform ance, plasm a stealth technologies, and directed high energy weapons. B AASS
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was contracted to the Defense Intelligence Agency (DIA) in 2008 to investigate and analyze the 
possibility of a credible threat posed by DAPs, To accom plish this m ission, B AASS over the 
past two years has focused on developing three separate resources, each unique to the study of 
U AP: 1) to obtain the m ost com prehensive suite of portable field sensors and personnel 
available, 2) to build the m ost all-inclusive database of U AP perform ance capabilities and 
behavior in the world and 3) to acquire world class com putational m ethodology for analysis of 
U AP data. This report touches on all aspects of these resources, but concentrates on the in-house 
com putational capabilities.
B AASS acquired the AN SYS M ultiphysics Finite Elem ent Analysis (FEA) program , for “a first 
of a kind” engineering and physics in-house resource devoted to providing a scientifically sound 
m athem atical analysis and m odeling of U AP behavior. Thus B AASS has acquired significant 
com putational capability to convert field data into m athem atical m odels and three dim ensional 
sim ulations.
This report provides theory, analytical and num erical solutions for selected U AP and U SO 
incidents through engineering and physics analyses. In particular, we exam ine a sentinel 
incident - the "Tic Tac" event - where F/A-l 8 aircraft from  a U nited States C arrier Strike G roup 
were vectored to a nearby unidentified contact in N ovem ber 2004. The white object observed by 
four F/A-l 8F aircrew was described as 40 feet in length and shaped and colored like a "Tic Tac" 
candy.
M any analyses of U AP m ay use analytical or closed form solutions to solve the equations that 
describe the physics of an event. W here analytical solutions do not exist or the geom etry is too 
com plex, AN SYS m ultiphysics provides a powerful com putational platform to solve large 
problem s num erically, while com bining and solving m any different physical equations.
C om pressible fluid flow analyses were perform ed to visualize the steady state pressure, 
tem perature and M ach num ber contours around two craft shapes. An incom pressible fluid flow 
problem  around a solid disc shaped object descending through the air into a body of liquid was 
investigated to observe the disturbance produced on the surface of the water. A successful 
analysis of a U SO was conducted using a full harm onic acoustics sim ulation; and com puted 
values showed good agreem ent with the expected theoretical solutions. An analysis of a 
spherical U AP radar cross section (RC S) was conducted using a full harm onic electrom agnetic 
sim ulation. Various other shapes of U AP and U SOs m ay be evaluated by applying boundary 
conditions and transient physics equations to obtain a better understanding of the capabilities of 
these objects.
B AASS em ployees and contractors com prise scientists, engineers, analysts, intelligence and 
investigative professionals with a wide range of technical capabilities and backgrounds. M any of 
the professional staff m em bers are considered national and international experts in their 
respective fields. B AASS’ personnel have experience in perform ing work for governm ent 
agencies such as the Departm ent of Energy and Departm ent of Defense. A broad m andate to 
research and develop future technology platform s pertaining to advanced propulsion, advanced 
non-aerodynam ic lift capabilities, future m aterial science breakthroughs including 
nanofabrication, novel power generation and signature reduction technologies, hum an interaction 
and effects of advanced technologies including field and radiation biological effects exists in
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B AASS’ work scope. B AASS’ vision is to identify and acquire disruptive or discontinuous 
technologies that will form the basis of aerospace and defense applications through the year 
2050, as well as those that pose potential threats to national security.
The com pany goal is to becom e a m ajor entity in the research and developm ent of future 
aerospace propulsion system s, controls, detection and tracking system s, stealth and directed 
energy uses by em ploying the best and brightest engineers and scientists available. The previous 
m entioned capabilities place B AASS in a strong position to provide technical results in both 
classified and unclassified endeavors.
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2. INTRODUCTION
2.1 H ISTORICAL EVENTS AND STUDIES
Disc, triangle, cigar and bell-shaped flying objects have been reported and docum ented on a 
global basis for m illennia. The sighting by 1843(a)(2)_____ on jurie 24. 1947 in the state of 
W ashington garnered unprecedented global m edia attention and began the m odern U FO era.
W hile flying near M t. Rainier, he observed a chain of nine unusual objects Hying from  north to 
1843(a)(2) south.|....- [reported that "two or three of them would dip or change course slightly, just 
enough for the sun to strike them  at an angle that reflected brightly on m y plane." The specific 
1843(a)(2)..term "flying saucer" was never used by I.... I however, he was quoted in a book stating: "As J 
described them at the tim e their flight was like speed boats on rough water or sim ilar to the tail
of a C hinese kite that 1 once saw blowing in the wind. As I put it to newsm en in Pendleton, 
Oregon, they flew like a saucer would if you skipped it across the water."11843(a)(2) Thus 
the m oniker "flying saucer" was bom . The term s "flying saucer" and "flying disc were used 
com m only and interchangeably in the m edia to describe what are now known as U FOs 
(U nidentified Flying Object). M any sightings of U FOs were reported by com m ercial and 
m ilitary pilots during the late 1940s and a flying saucer allegedly crashed outside of Roswell,
N ew M exico, in early July 1947.
Shortly thereafter, a series of sightings of "green fireballs" began. These reports were alm ost 
exclusively over the state of N ew M exico. Increasing significantly in num ber by Decem ber 
1948, these sightings typically occurred over sensitive governm ent installations, m ost notably the 
Los Alam os and Sandia N ational Laboratories. An investigation was initiated by m eteor expert 
843(a)(2)_______ After personally witnessing a green fireball four to five degrees above the
horizon on a horizontal trajectory on Decem ber 12, 1948| -.....concluded the fireballs were...'843(a)(2)
structured, that is, not atm ospheric phenom ena. Initially they were thought to be of Russian
origin. In April 1950, Project Twinkle was created to be a network of stations with the purpose 
of observing, studying, and collecting data on the firehall phenom ena. This project did little to 
solve the m ystery, and was disbanded later that year. Large num bers of U FO sightings 
continued in the late 1940s and as a result, som e unease about the nature of the objects began to 
escalate in m ilitary circles, notably in the Air Force. For exam ple, in Septem ber 1947, Air Force
1843(a)(2) issued a m em orandum stating "The reported operating characteristics
such as extrem e rates of clim b, m aneuverability (particularly in roll), and m otion which m ust be 
considered evasive when sighted or contacted by friendly aircraft and radar, lend belief to the 
possibility som e of the objects are controlled either m anually, autom atically or rem otely." 
^®*^®IL.. ....recom m ended a detailed study of the U FO phenom enon. B ased on increasing concern
on the part of the m ilitary, the U .S. governm ent initiated official studies of U FOs.
Project Sign was the first official U .S. governm ent study of U FOs perform ed by the U nited 
States Air Force in early 1948 and concluded in early 1949. Project Sign officials argued U FOs 
were likely of extraterrestrial origin, and m ost of the project's personnel cam e to favor the 
extraterrestrial hypothesis. This hypothesis was rejected by the senior Air Force personnel. 
Project Sign eventually cam e to no official conclusion about U FOs with the final report stating 
the existence of flying saucers could neither be confirm ed nor denied. Project Sign was 
concluded and restarted as Project G rudge in February 1949.
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Project G rudge attem pted to give each and every case a solution or an identifier tag. G rudge 
existed in various form and nam e until project com pletion in M arch 1952. The final Project 
G rudge report stated 22% of cases were categorized as unidentified, 69% identified, and 9% 
contained insufficient inform ation to categorize.
In M arch 1952 Project B lue B ook replaced G rudge and rem ained headquartered at the Air 
Technical Intelligence C enter at W right-Patterson Air Force B ase in Ohio. Over the next 
seventeen years. Project B lue B ook recorded approxim ately 15,000 U FO incidents, and B lue 
B ook reported 701 of these incidents as "unidentified." The dram atic strike in U FO siizhtines in 
1952 prom pted the C IA to convene a scientific panel,P^^_________________________ in
January 1953 to exam ine recent U FO data. It is widely stated am ong m odem day U FO 
organizations that the 1843(a)(2) advocated a cam paign to "debunk" U FOs.
B eginning on N ovem ber 1, 1966, the Air Force Office of Scientific Research awarded $313.000
to a research team at the U niversity of C olorado. 1843(a)(2) to
study the scientific im plications of U FOs. The study was undertaken on the m aterial furnished by
Project B lue B ook. The 1843(a)(2) final (and controversial) conclusion stated “we
have recom m ended against the m ounting of a m ajor effort for continuing U FO study for 
scientific reasons.” [1843(a)(2) | announced B lue B ook 
would be closed due to the fact further funding "cannot be justified either on the grounds of
national security or in the interest of science." The last publicly taken report for project B lue 
B ook operations was Decem ber 17, 1969, but officially it closed on January 30. 1970.
Since the end of B lue B ook num erous organizations have taken on the role of U FO/UAP 
investigations. Few of these groups have been professionally organized, trained, or equipped to 
properly investigate the phenom ena. In contrast, one purpose of this report is to show B AASS is 
on the route to being the leading force in com plete investigation and scientific analysis of the 
phenom ena.
2.2 BAASS’ TWELVE TECH NOLOGY FOCUS AREAS
B AASS is a research organization focused on the identification, evaluation, and acquisition of 
novel and em erging future technologies worldwide as they specifically relate to air and space 
craft. C utting edge research areas include propulsion system s, space applications of nanosensors, 
piezoelectric and nano wire fabrics, hum an perform ance, plasm a stealth technologies, and 
directed high energy technologies.
Research and developm ent necessary for the procurem ent of the technology required for 
advanced space and weapons system s is conducted through use of com putational M ultiphysics 
FEA program s, developm ent of com puter code, experim entation, m aterial science testing and 
m anufacturing of prototypes in B AASS/B igelow Aerospace in-house and in collaborating 
facilities and laboratories. Research areas of interest include C om putational Fluid Dynam ics, 
Heat Transfer, N uclear Engineering. Electrom agnetics and Radio Frequencies, Theoretical and 
C om putational Physics, B iological Sciences and C hem istry.
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Research perform ed through theoretical and com putational applications, as well as m odeling of 
com ponents of non-conventional propulsion system s is under way to provide for future 
developm ent of vehicles capable of operating in the atm osphere, under water and in space. 
B AASS research intends to provide innovative approaches and concepts for aircraft, propulsion, 
and flight technologies dem onstrating significant advances in perform ance and capabilities 
beyond those in operation today.
B AASS’ twelve key technology areas concentrate on how breakthrough technologies will 
provide for the developm ent of advanced spacecraft concepts and weapon technologies through 
the year 2050 and beyond. The twelve areas are:
1. Lift
2, Propulsion
3. C ontrol
4. Power G eneration
5. Spatial Tem poral Translation
6. M aterials
7. C onfiguration, Structure
8. Signature Reduction
9. Hum an Interface
10. Hum an Effects
11. Arm am ent
12. Other Peripheral Areas
2,3 BAASS PERSONNEL, SOFTWARE, EQUIPMENT AND DATA WAREH OUSE
Although the m ajority of this report is devoted to dem onstrating B AASS’ capabilities in 
m athem atical m odeling of various U AP perform ance param eters, the next section provides a 
short sum m ary of som e of the B AASS personnel, portable data collection sensors, as well as the 
current B AASS in-house database architecture.
2.3.1 BAASS Personnel
B AASS em ployees and contractors com prise scientists, engineers, analysts, intelligence and 
investigative professionals from diverse backgrounds, A m ajority of B AASS personnel have 
perform ed work for governm ent agencies such as the Departm ent of Energy and Departm ent of 
Defense, -
Research and developm ent necessary for the procurem ent of the technology required for 
advanced space and weapons system s is conducted by num erical com putational analysts through 
use of com putational m ultiphysics FEA program s. Application and scientific program m ers are 
involved in developm ent of com puter code that drives data m ining and scientific applications 
used to evaluate historical and present U AP cases. Professionals in all areas conduct 
experim entation, m aterial science testing and m anufacturing of prototypes in both in-house 
facilities and collaborating facilities and laboratories. Areas of concentration include
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C om putational Fluid Dynam ics (C FD), Heat Transfer, N uclear Engineering, Electrom agnetics 
and Radio Frequencies (RF), Theoretical and C om putational Physics, B iological Sciences and 
C hem istry.
2.3.2 ANSYS Multiphysics FEA
The AN SYS W orkbench platform is a powerful m ulti-dom ain sim ulation environm ent that 
harnesses the core physics from AN SYS, enables their interoperability, and provides com m on 
tools for interfacing with C AD, repairing geom etry, creating m eshes and post-processing results. 
To our knowledge, this powerful com putational capability has not been previously utilized in the 
64 year history of U FO study. It is hypothesized that through this m ore broad ranging analysis, 
additional theoretical constructs can be generated regarding U AP and U SO behavior. These in 
turn can provide the scaffolding for advanced engineering concepts.
2.3.3 Equipment
2.3.3.1 Field Investigative Equipment
B AASS has am assed a considerable am ount of field investigative equipm ent. The inventory 
includes a variety of im aging devices, along with G lobal Positioning System s (G PS) and range 
finding item s. Of note are the following:
2.3.3.1.1 Canon 51) MK II Digital SLR Cameras
Two C anon 5D M K II, 21.] M egapixel, Digital SLR cam eras were selected based on their 
capability for low light photography when com bined with the C anon EF 300 m m ultrasonic, and 
the C anon EF 24-105 m m ultrasonic lenses. The 21.1 M egapixel size allows for RAW im ages 
suitable for scienlilic exam ination and analysis.
2.3.3.1.2 Sony A350 Digital SLR camera
The Sony A350 is a 14.2 M egapixel, digital SLR cam era, with a Sony N 50-300 m m , a 
SonyN 50-70 m m lens, and a Sony M acro 2.8/50 m m lens. The a350 while a high quality 
cam era, is com pact and portable. It also allows for close-up and one-to-one photography.
2.3.3.1.3 Sony H igh Definition Video Cameras
Three Sony High Definition Video (IIDV) 1080i, High Definition Video cam eras, with low light 
capability were chosen for video capture in various field conditions.
2.3.3.1.4 Sony H andicam, Digital Video Cameras
Four Sony Handicam , digital video cam eras with 80 G B hard drive storage capacity. These 
cam eras are com pact and portable, and using the HDD allow for up to 4 hours of continuous 
video recording with no tapes or other external m edia. They can also capture still im ages.
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2.3.3.1.S ATT PVS-7, Night Vision Devices
Seven ATT PVS-7, N ight Vision Devices - m ilitary quality, state-of-the-art night vision devices.
2.3.3.1.6 Oasys Universal Thermal Monocular (UTM)
This device is a ruggedized therm al im aging and designation system . It includes a digital 
m agnetic, both still and video capture capability as well as a digital PC interface allowing for 
real-tim e review of im ages in the field.
2.3.3.1.7 Garmin Global Positioning Systems
One C olorado 400t and two Oregon 400t. G lobal Positioning System s, allowing for route 
m apping as well as waypoint storage in the field.
2.3.3.1.8 Leica Rangemaster 1200 Laser Range Finders
These two range finders arc accurate out to 1500 m eters, extrem ely com pact and user friendly.
2.3.3. L9 Sony CyberShot Cameras
Three Sony C yberShot 10.1 m egapixel digital cam eras - com pact and portable for quick reaction 
to opportunities while actively investigating.
These equipm ent item s give B A  ASS considerable capability when investigating events in the 
field. In addition to the item s listed above a wide range of other support type item s arc in the 
B AASS inventory. These include Toshiba laptop com puters, digital voice recorders, digital 
G am e C am eras, 1R spot lights, power invertors, several pieces of older night vision equipm ent, 
and packaging and storage item s for solid, liquids, and hazardous m aterials.
In addition, B AASS obtained Technical Surveillance C ounterm easures (TSC M ) equipm ent in an 
effort to enhance the security of B AASS facilities. In addition to the below listed TSC M  
equipm ent B AASS personnel are trained by Research Electronics International in C ookeville, 
TN ; also the m anufacturer of the equipm ent.
• OSC OR 5000E, Om ni-Spectral C orrelator covering the radio frequency range from  
50 kHz to 3 G Hz
• ORION  N on-Linear Junction Detector
• TALAN  Telephone Analyzer
• C PM -700 B roadband Detector
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23.3.2 Scientific Equipment
233.2.1 Vcho VMS-001 200X 13 Megapixel Digital USB Microscope
This instrum ent is a very portable (4.4 x 13 inches) digital m icroscope which expands the 
capability of the field investigators. The m icroscope allows detailed im ages to be taken and 
connects directly to a laptop. Illum ination is via 4 built in white LED lights.
233.2.2 Celestron 44340 3.5” LCD Digital Microscope
This instrum ent is a bench top digital m icroscope. The m icroscope has m agnification 
capabilities ol'40-400X extending up to 1600X with digital zoom . Im ages can be uploaded to a 
PC  or laptop via a U SB  connection. Il could also be taken into the field if required.
23.3.23 Niton XL3t 900S GOLDD Analyzer
This instrum ent is an X-ray fluorescence (XRF) analyzer. The device analyzes the em ission of 
characteristic "secondary" (or fluorescent) X-rays from a m aterial that has been excited by 
bom barding with high-energy X-rays. B AASS field team s deploy the N iton and conduct on-site 
elem ental analysis.
233.2.4 Colibri TTC H andheld Dose Rate Meter
This instrum ent package allows for the detection and quantification of alpha, beta and gam m a 
radiation in the field. The ability to accurately m easure and quantify these three types of 
radiation adds another critical level of capability to the B AASS arsenal of analysis.
233.2.5 H and held Spectrum Analyzer Pro Bundle 3 (NF-5030 and H F-60100)
These are instalm ents designed to detect and m easure a broad spectrum of electrom agnetic 
(EM F) radiation and high frequency radio waves. The N F-5030 m easures three dim ensional 
m agnetic fields from as low as background up to 20 G auss. C om bining the two instrum ents 
electric fields are m easured from  0,1 V/m  to 20 kV/m  and frequencies from 1 Hz to 9.4 G Hz.
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2.33.6 H ardware for ANSYS Workbench Platform
The research and work perform ed by B AASS ranges from technical design and prototyping, all 
(he way up to advanced theoretical and com putational studies of partial differential equations 
describing m ultiphysics problem s. An expandable twelve core Hewlett Packard server with 
48 G B of RAM  and 1 TB of storage is used to perform parallel processing solutions for 
structural, fluid flow, heat transfer, high and low frequency electrom agnetic problem s along with 
coupled physics of two or m ore of those listed previously.
23.4 Data Warehouse
AAP Person 
5, AAP 
Person 58
B AASS developed a Data W arehouse to support research on U AP and related anom alies and 
titled it "Project C APELLA”, The B AASS Data W arehouse is revolutionary because it: 1)
incorporates a form at based on the Six Layer M odel for analyzing U AP, 2)
includes several new databases developed by B AASS, and 3) includes databases developed by 
others which have never been collectively analyzed. The Data W arehouse currently consists of 
eleven separate databases and their associated supporting docum entation in electronic form at 
such as witness interviews, photographs, videos, recordings, sketches, analytical reports, etc. 
Each of the databases contains U AP sighting events relating to the purpose of that particular 
database, although som e of the reported cases do overlap. Four of the databases will continue to 
catalogue current and future sighting reports. Seven of the databases have been com pleted and 
fully integrated and populated with all pertinent inform ation captured by the C APELLA form at. 
B AASS will continue to input historical data in the C APELLA form at and will expand the Data 
W arehouse with additional databases and unusual aerial phenom ena inform ation.
The eleven databases currently included in the Data W arehouse are:
I. N I DS Database
2. 1843(a)(2) pj]01 Database
3. Sign/G rudge/B lue B ook Database
4. U FOC AT Database
5. M U FON C ase M anagem ent System Database
6. Project C olares Database
7. C anadian Release Database
8. U nited K ingdom  Release Database
9. B AASS Database
10. U tah Ranch Database
11. Post-U tah Ranch Elfects Database
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The B AASS Data W arehouse is an electronic repository for historical, ongoing, and future U AP 
reporting and investigations. The Data W arehouse is designed to facilitate sophisticated analyses 
and data m ining to im prove our understanding of the extent, structure, and frequency of U AP, as 
well as their potential correlation to known physical, environm ental, biological, or socio-political 
factors.
23.4.1 CAPELLA Format M P Person
5, AAP
The C APELLA database form at is based upon the "Six Layer M odel for Anom alous Pef^son 58 
Phenom ena" developed by |AAP Person 5 | and |AAP Person 58 ]| ' I
This six layer m odel encapsulates all of the potential characteristics of U AP events that can be 
studied. The six layers are:
1. The Physical Layer - those physical characteristics associated with a U AP event
2, The Anti-Physical Layer - the patterns that conflict with those predicted in m odem  physics
3. The Psychological Layer - the psychological im pacts to the witness(es) and the social 
conditions that surround them
4. The Physiological Layer - the effects perceived by hum ans
5. The Psychic Layer — the effects com m only found in parapsychology literature
6. The C ultural Layer - the prim ary and secondary effects upon society.
Additionally, the C APELLA form at captures adm inistrative details associated with the U AP 
event, such as witness inform ation, location, date, tim e, duration, etc.
23.4.2 Data Warehouse Upgrade
B AASS is undergoing a database upgrade project to further enhance data security and integrity, 
and increase processing power for greater analytical capability. The C APELLA fram ework and 
m ethodologies will be preserved in the upgraded system . This upgrade will increase efficiency 
and effectiveness, and will allow databases to be analyzed individually or collectively.
23.4.3 Statistical Analysis
B AASS has com pleted a first-level, yet com prehensive statistical analyses for three of the 
databases: 1S43(a)(2) pj|ot Database, Project Sign/G rudge/B lue B ook Database, 
and the U tah Ranch Database. Tne analyses on th( 1S43(a)(2) anj p|ue Qo^ databases are 
focused on identifying patterns of technical inform ation from the case reports. The U tah Ranch 
analysis delves into patterns and aspects of when anom alous activity is reported in an attem pt to
identify potential tim es and im prove the m eans of future detection m ethods.
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3. TYPES OF UAPS OBSERVED
N ASA aeronautical engineerf1843(a)(2) | m ade im portant inroads into attem pts to delineate
som e quantitative characteristics of U FO perform ance by close exam ination of. and derivation of 
num erical param eters from well investigated sentinel U FO casesM  843(a)(2) ]n addition, 
com puter scientist____________ has attem pted to com pute estim ates of optical power
output derived from U FO reportsp^P Person 5 J This report attem pts to extend and broaden 
these prelim inary studies using considerably enhanced com putational power and m athem atical 
m odeling capabilities.
Figure I, taken from  
U AP phenom ena.
1843(a)(2) depicts illustrations of the various shapes associated with the
F igure 1. The UF O Pa ttern: A C ond ensed S ta tement of Repea ted Observa tions
As an im portant com ponent of these studies, B AASS understands a considerable num ber, 
possibly a m ajority, of U AP reports can be explained by sim ple m isidentification of current 
advanced technology platform s. Som e recent black triangle and even possibly som e saucer and 
hat shaped U AP reports over the last several decades m ay have been explained by aircraft 
sightings of the Lockheed SR-71 B lackbird (Figure 2), Lockheed F-117 N ighthawk Stealth 
Fighter (Figure 3), N orthrop G rum m an B -2 Spirit Stealth B om ber (Figure 4) and B oeing 
Phantom W orks Stealth X-45A U nm anned Arial Vehicles (U AV) (Figure 5). N evertheless, a 
significant num ber of cylindrical and cigar shapes along with spherical, lenticular and ellipsoid
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shaped U APs which appear to hover and/or accelerate at rapid rates from a stationary position 
have been harder to explain considering the inherently poor aerodynam ic properties of these 
objects. It is this latter subset of U AP reports that B AASS has focused on.
F igure 2. Lockheed M a rtin S kunk W orks S R-71 Bla ck Bird
F igure 3. Lockheed F -117 Nightha wk S tea lth F ighter
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F igure 4 Northrop Grumma n B-2 S pirit S tea lth Bomber
F igure 5 . Boeing Pha ntom W orks B-2 S tea lth X -45 A UAV
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F igure 6 . Three D imensiona l Rend ering of a C ylind rica l or "Tic Ta c" UAP
F igure 7. Three D imensiona l Rend ering of a M eta llic S pherica l UAP
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4. ANALYTICAL AND NUMERICAL SOLUTIONS FOR UAP INVESTIGATIONS
4.1 "TIC TAC" INCIDENT
The following sum m ary is excerpted from  the report of an investigation conducted by personnel 
assigned to DIA of an observation by elem ents of the N im itz C arrier Strike G roup of U AP off 
the coast of M exico in N ovem ber 2004. N ote: The DIA personnel who wrote the report utilized 
the term Anom alous Aerial Vehicle (AAV) rather than the m ore com m on U nidentified Aerial 
Phenom enon (U AP) or U nidentified Flying Object (U FO). All three term s, AAV, U AP, and 
U FO are used at different tim es in this section and should be considered interchangeable.
During the period of approxim ately 10-16 N ovem ber 2004, the N im itz C arrier Strike G roup 
(C SG ) was operating off the western coast of the U nited States in preparation for their 
deploym ent to the Arabian Sea. The U SS Princeton on several occasions detected m ultiple 
Anom alous Aerial Vehicles (AAVs) operating in and around the vicinity of the C SG . The AAVs 
would descend "very rapidly" from  approxim ately 60,000 feet down to approxim ately 50 feet in 
a m atter of seconds. They would then hover or stay stationary on the radar for a short tim e and 
depart al high velocities and turn rales. On 14 N ovem ber after again detecting the AAV, the 
U SS Princeton took the opportunity of having a flight of two F/A-18Fs returning from  a training 
m ission to further investigate the AAV. rhe U SS Princeton took over control of the F/A-18s 
from  the E-2C  Airborne Early W arning aircraft and vectored in (he F/A-I8s for intercept leading 
to visual contact approxim ately one m ile away from the AAV, which was reported to be "an 
elongated egg or a ‘Tic Tac' shape with a discernable m idline horizontal axis," It was “solid 
white, sm ooth, with no edges. It was “uniform ly colored with no nacelles, pylons, or wings," It 
was approxim ately 46 feel in length, The F/A-18Fs radar could not obtain a 'lock’ on (he AAV; 
however it could be tracked while stationary and at slower speeds wilh the Forward Looking 
Infrared (FLIR). The AAV did take evasive actions upon intercept by the F/A-18 dem onstrating 
an advanced acceleration (g), aerodynam ic, and propulsion capability. The AAV did not take 
any ofl'ensive action against the C SG ; however, given its ability to operate unchallenged in close 
vicinity to the C SG it dem onstrated the potential to conduct undetected reconnaissance leaving 
the C SG with a lim ited ability to detect, track, and/or engage the AAV.
According to 1843(a)(2) the AAVs would descend from a very high altitude into the 
scan volum e of the AN /SPY-I at a high velocity. The top of the scan volum e would put the 
AAVs at higher than 60,000 feel. The AAVs would descend “very rapidly” from approxim ately 
60,000 feet down to approxim ately 50 feet in a m atter of seconds. They would then hover for a
short tim e and depart at high velocities and at turn rales dem onstrating an advanced acceleration
(g) capability. 1843(a)(2) added that based on his experience, which is 17 years as a Fire 
C ontrol on Aegis cruisers, the aaV exhibited ballistic m issile C haracteristics in reference to its
appearance, velocity, and indications on the radar. Since the radar was in (he m ode to handle Air 
Intercept of conventional aircraft it never obtained an accurate track of the AAVs and was 
quickly “dropped" by the radar m eaning it was elim inated by the com puter to reduce the am ount
of clutter on the radar, as any other false target is handled. If the radar were set up in a m ode for 
B allistic M issile tracking they likely would have had the capability to track the AAV. They were 
delected three separate tim es during the week operating oft'the western coast of the U nited States 
and M exico, The Tactical Air Officer onboard the Princeton could not identify the radar contact
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and given the high speed and altitude was perplexed. On 14 N ovem ber 2004. after again 
detecting an AAV took the opportunity of two F/A-18s airborne in the vicinity to task them for 
airborne reconnaissance of the AAV.
F igure 8 Loca tion of the AAV  d uring the F /A18 Intercept
AAP Person 9 J, was Hying a single seat 
F/A-18C  that launched from the U SS N im itz at approxim ately 1030L to conduct a Functional 
C heck Flight of an aircraft that had recently com pleted significant m aintenance. He noted the 
weather that day was blue skies, no clouds, and unlim ited visibility. After 30 m inutes into his 
flight he received a radio call from his air controller asking him to investigate an unidentified 
airborne contact. This was not a standard request. Additionally the controller asked if he had 
ordnance onboard, which was odd since no controller had ever asked that question during a
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situation of identifying an unknown contact over U .S. or International territory. He responded 
that he had no ordnance onboard. The controller provided vectors to the vicinity of Figure 8. 
The object was reported to be at “slaw speed and low altitude.”
W hile en route at approxim ately 250 knots indicatcd/400 knots groundspeed at m edium  altitude 
(15-25,000 feet), he gained radar contact of what he believed to be two F/A-18Fs that were 
approaching the AAV from  the west at low altitude (500- 5,000 feet). There was no other traffic 
on the radar. The controller inform ed him  to rem ain above 10,000 feet, as there was other fighter 
traffic at low altitude investigating the AAV. As he approached approxim ately 15nm from the 
AAV descending through approxim ately 15,000 feet, he could see a water disturbance in the 
ocean surface. He recalled that the sea state was low (calm ). At approxim ately 5-10 nm away 
from  the AAV, the controller told him  to "skip it” and return to his operating area. Since he was 
close he elected to fly over the water disturbance to try and see what was causing it.
The disturbance appeared to be 50 to 100 m eters in diam eter and close to round. It was the only 
area and type of whitewater activity that could be seen and rem inded him  of im ages of som ething 
rapidly subm erging from the surface like a subm arine or ship sinking. It also looked like a 
possible area of shoal water where the swell was breaking over a barely subm erged reef or 
island. He overflew the disturbance and turned back to the northwest. As he was flying away he 
could see the disturbance clearing and could no longer identify the place where it occurred. He 
did not see any object or vessel associated with the disturbance either above the surface, on the 
surface, or below the surface. He also never m ade visual contact with the other fighter aircraft 
that were vectored to the location or the AAV. It is possible that the disturbance was being 
caused by an AAV but that the AAV was ‘cloaked’ or invisible to the hum an eye.
|AAP Person 9 [recovered aboard the N im itz at approxim ately 1200L. He reported to the C arrier 
Intelligence C enter (C VIC ) and was asked by his Intelligence Officer. 1843(a)(2) if he 
saw the “supersonic Tic Tac"? W e questioned now 1843(a)(2) to determ ine 11 tic had any further 
inform ation but based on his position in C VIC  at the tim e he was not involved in any further 
discussions concerning the AAV.
1843(a)(2) I Ie and
1843(a)(2) [were in the lead aircraft of the first F/A-18F section airborne 
that day trom VFA-41, [1843(a)(2) | The flight walked, started and launched with no 
issue. They com pleted their departure from the U SS N im itz and flew to the working area to 
conduct the training portion of the flight. After they com pleted their training the E-2C  controller
handed them  off to the U SS Princeton|i843(a)(2) where they received vectors via B earing
1843(a)(2)
Range Altitude Aspect (B RAA) to an unknown contact flying into the working area from the 
' ‘asked what ordnance they had on board. [1843(a)(2) |told| [control that 1843(a)(2) 
they had two captive training AIM -9M s (C ATM -9) and no other ordnance. The flight descended
south.
to between 20-24,000 feet and proceeded to the contact. 1843(a)(2) did not recall any
indications via on-board sensor of the object. Their aircraft was not carrying a Forw ard Looking
Infrared (FLIR) pod onboard. As 1843(a)(2) 
(no targets). ------------
rem em bers it, the radar Attack Display was clean
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_ png |were attem pting acquire the object visually as they heard “m erge 
'643':a)^ plot" from | | According to| 1843(a)(2) |the first indication he had of the unknown contact 
was a visual of a disturbance on the water below the AAV. As he scanned the area he gained a 
visual on the object. It is im portant to note that when asked to describe the disturbance on the 
waler he staled that it was localized underneath the object, did not appear as a trail or wake, and 
looked like frothy waves and foam  alm ost as if the water was boiling.
A* this point 1843(a)(2) detached p843(a)(2) [which held at approxim ately 20,000 feet, 
and 1843(a)(2) descended to between 12-16,000 feet. 11843(a)(2) [attem pted a "helm et 
lock’ that was unsuccessful. Il is im portant to note ihat [1843(a)(2) was using the Joint Helm et 
M ounted C uing System  which will cue the aircraft sensors sucti as the radar to ‘lock on’ to what
1843(a)(2)
the pilot is looking at and it also has a recording capability. It m ay have been useful in this 
situation but typically because of the large am ount of head m ovem ent it is not practical. [1843(a)(2)
{
stated that the helm et’s recording capability was rarely used therefore he did not think to 
tat day.
1843(a)(2) com m unicated what they were seeing with [ 
running dialogue on the interflight radio with|l843(a)(2)
control and said that he had a 1843(a)(2) 
~ ’ Hstated that the object
1843(a)(2)
was “holding like a Harrier.” (Referring to the AV-8B  jet aircraft, which is capable of hovering
and Vertical/Short Takeoff and Landing (V/S fOL) via thrust vectoring.) According to I 1843(a)(2)
the object’s shape was like an elongated egg or a ‘Tic Tac’ and had a discernable m idline
horizontal axis. However, the object was uniform ly white across the entire body. It was
approxim ately 46 feet in length. [1843(a)(2) [described it as “solid white, sm ooth, with no 
edges. It was uniform ly colored with no nacelles, pylons, or wings.” W hen asked to describe
the appearance, if it glowed or reflected sunlight he said, "neither, it looked like it had a white 
candy-coated shell, alm ost like a white board.” His report differs from 1843(a)(2) in that he
reported the object traveling level at approxim ately 500-1000 feet at approxim ately 500 knots.
The object was pointed in a north/south orientation and was m oving both north & south and east 
& west, whi c m aintaining a consistent altitude. These displacem ents, according to 1843(a)(2) 
were m inor. 1843(a)(2) [ stated he then began a descent with the intention to take a close aboard
1843(a)(2)
pass with the object in an attem pt to visually identify it. They began the decent as they rolled in 
from  about 10,000 ft and approxim ately 350 knots to take the object close aboard. 1843(a)(2) 
pulled nose on and then pulled trail (aft) of the object. As they were m aneuvering, the object 
appeared, according to|i843(3)(2) [’ to recognize us.” He assessed this from  the fact the object
“pointed” (realigned its axis) in the direction of their aircraft. At this tim e, according tc 
the disturbance on the water ceased.
1843(a)(2)
As they com pleted this m aneuver, the object ascended quickly and pulled lift vector on and aft of 
them at a supersonic speed. 1843(a)(2) com m anded the radar through the Short Range radar 
set and asked for a picture from [1843(a)(2) [initially reported that the “picture was clean” (no 
contact) but then stated “you’re not going to believe this, it's al your C AP” m eaning that the
AAV had flown to their training C AP, which was located in the southern end of the (raining area 
and had clim bed to approxim ately 24,000 feet. [1843(a)(2) [stated that the flight attem pted to 
locate both the object and the disturbance with no success. [1843(a)(2) [stated that nothing was 
seen on the surface or subsurface and that there were no indications of the previous disturbance.
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Following the engagem ent, the flight rejoined and returned to the U SS N im itz. W hen asked how
the jets functioned and if there was any indications of a system m alfunction, he stated that, “the
jets were brand new, less than 100 hrs on them .
They were working perfectly.” 1843(a)(2) when asked, said that all aircraft system s were 
functional, Thal there were no m ission com puter issues or avionics issues and that there was no
radio or com m unication interference and that they had entry into the Link-16 network. W hen 
asked, 1843(a)(2) couldn't confirm  any physiological or psychological feelings that were out 
of the ordinary.
1843(a)(2)
1843(a)(2) , - ______was a m em ber of VFA-41 and was the 1843(a)(2)_________________
Hying witl{1843(a^) ] They were a part of the second F/A-18F section airborne
that day from VFA-41. Their flight launched following the 1843(a)(2) [flight. The crews 
spoke with each other in the paraloft, discussed the object and that the flights were scheduled for 
the sam e working area. 1843(a)(2) [flight told[1843(a)(2) flight what they saw and to 
try to see and record what they could.
There were no clouds and there was a discernable horizon. The tim e was approxim ately 1500L. 
All on board system s were functioning norm ally. The radar was in a standard search m ode 
(RW S/ 80N M / 4bar/ intr) and the FLIR was in L+S slave (the FL1R would point in direction of 
an L+S track). There was no radio or com m unication interference and they had entry into the 
Link-16 network. Initial awareness of an object cam e via the radar. According to the radar i843(s!(2) 
display, the initial tracks were at approxim ately 30-40 nm to the south of the aircraft. " .... 
1843(a)(2) was controlling the radar and FLIR and attem pted m ultiple tim es to transition the 
radar to Single Target Track (STT) m ode on the object. The radar could not take a lock, the 
h-sweep would raster around the hit, build an initial aspect vector (which never stabilized) and 
then would drop and continue norm al RW S b-sweep. W hen asked, 1843(a)(2) [stated that 
there were no jam m ing cues (strobe, cham pagne bubbles, “any norm a EA indications”). It “just 
appeared as if the radar couldn't hack it.” The radar couldn’t receive enough inform ation to 
create a single target track file. The FLIR, in L+S slave, pointed in the direction of the initial 
track flies as the radar attem pted lock. The FLIR showed an object at 0 ATA and approxim ately 
-5 deg elevation (Figure 9). According to| 1843(a)(2) '“the target was best guess co-altitude
or a few thousand feet below,” estim ating the object to be between 15-20 thousand feet. The 
object, according to the FLIR, appeared stationary (Figure 10). There was no discernable 
m ovem ent from the object with the only closure being a result of the aircraft's m ovem ent. As 
1843(a)(2) [watched the object it began to m ove out of FLIR field of view to the left. | 31843(a)(2) 
1843(a)(2) m ade no attem pt to slew the FLIR and subsequently lost situational awareness to the 
object. The Flight continued with training m ission with no further contact with object.
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F igure 9 . F LIR in 'W hite H ot' M od e
F igure 10 F LIR in "Bla ck H ot" mod e
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1843(a)(2) | was clear in that he couldn’t confirm  that it was the sam e object as described by 
1843(a)(2) I flight. U e never had visual, only seeing the object via the FLIR. He reaffirm ed 
that all system s were functional. Following com pletion of the training portion, the section 
returned to the ship for a norm al approach, landing and shutdown. The crew m et in C V1C  and 
debriefed.Q£43(a)(2r2^ said that the C IVC section attem pted to collect his tapes but he 
refused.
They proceeded to their ready room where they debriefed with and his flight
C opies of the tapes were m ade with a set being turned into the intelligence section. .... 1843(a)(2) 
1843(a)(2) was noj asked to sign any non disclosure agreem ent and he is uncertain how far up
the chain the reporting went past his com m anding officer. W hen asked|1843(a)(2) ~| couldn’t
confirm any physiological or psychological feelings that were out o' the ordinary. He only
expressed a feeling of confusion during the event.
According to form er 1843(a)(2) ] now a civilian working for^^^ who was a
|1843(a)(2) ~| onboard the Louisville in N ovem ber 2004 during the AAV activity 
there were no unidentified sonar contacts in the vicinity of the aerial sightings or anytim e during 
the operations off the coast of C alifornia. The form er 1843(a)(2)
1843(a)(2) confirm ed that there was no anom alous undersea activity during this period. There
was a live lire exercise conducted by the U SS Louisville during the period of and in the vicinity
of the AAV sightings: however, the weapon in use did not m atch the flight profile or visible 
characteristics of the AAV. Additionally any live lire would have been coordinated throughout 
the C SG and all air traffic would have been well aware of the launch and operation of the 
weapon system . Aircraft would not have been vectored for the intercept of a U S W eapon in 
flight. B ased on the lack of detection of any unidentified sonar contacts it is highly unlikely that 
an AAV operated below the surface of the ocean; it is possible that the AAV dem onstrated the 
ability to be cloaked or invisible to the hum an eye based on pilot reporting of the water 
disturbance with no visible craft. B ased on the assessm ent of 1843(a)(2) if the AAV did 
operate underwater undetected it would represent a highly advanced capability given the 
advanced capability of our sensors.
Key Assessments According to D IA Report
• The Anom alous Aerial Vehicle (AAV) was no known aircraft or air vehicle currently in 
the inventory of the U nited Stales or any foreign nation.
■ The AAV exhibited advanced low observable characteristics al m ultiple radar bands 
rendering U S radar based engagem ent capabilities ineffective.
• The AAV exhibited advanced aerodynam ic perform ance with no visible control surfaces 
and no visible m eans to generate lift.
■ The AAV exhibited advanced propulsion capability by dem onstrating the ability to 
rem ain stationary with little to no variation in altitude transitioning to horizontal and/or 
vertical velocities far greater than any known aerial vehicle with little to no visible 
signature.
• The AAV possibly dem onstrated the ability to ‘cloak’ or becom e invisible to the hum an 
eye or hum an observation.
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The AAV possibly dem onstrated a highly advanced capability to operate undersea com pletely 
undetectable by our m ost advanced sensors. The so called “Tic Tac” incident has m any physics 
and engineering aspects that m ay be studied with regards to understanding the perform ance 
capabilities and propulsion m echanism s of the craft. Since there was little hard data, m ost 
analyses of the incident had to be m ade using either param etric studies or assum ptions based on 
eye witness testim ony.
4.1.1 Analytical Solutions of Velocities and Accelerations Associated with "Tic Tac" 
Performance
An initial starting point consisted of using basic physics form ulas for the calculation of velocities 
and accelerations based on the distance s the object traveled and the duration tim e t of the 
incident. Since no exact duration was known, as the radar operator noted that it occurred in a 
m atter of "seconds," a param etric range from 0.5 seconds to 10 seconds was studied (assum ing 
instantaneous velocities and accelerations).
ds 
v~di
dv 
a = — dt
Flight is classified in six categories as shown in the table below.
Ta ble 1. M a ch Regimes
Regime Subsonic Transonic Sonic Supersonic Hypersonic High-hypersonic Re-entry 
Speeds
Mach 
Number <10 08 12 1.0 1.0 -5  0 5 .0 - 10.0 10 0-25 .0 >25 .0
Due to the lack of data, only the instantaneous velocity of the craft v and the instantaneous 
acceleration a, were com putable. For the velocity and deceleration witnessed, a negative sign is 
im plied to represent the direction com ponent of the vector.
Assumptions:
1. Elevation of 60 ,0 0 0  ft to Sea Level - It was reported by radar observation the object 
descended from  approxim ately 60,000 ft to sea level in a m atter of seconds.
2. M atter of Seconds - A range of 0.5 seconds to 10 seconds was used for a param etric 
study.
4.1.2 Summary of Analytical Velocity and Acceleration Solutions
Table 2 provides the com puted values of instantaneous velocities and decelerations in ft/s and 
m ph and ft/sec2 and g respectively for each chosen At. Figure 11 through Figure 14 show
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N ovem ber 23, 2010


non-continuous plots for velocity and acceleration in each unit for a specific At event duration. 
As one m ay observe from the table and graphs, extrem ely sm all and sm all duration tim es 
specifically between 0.5 and 5 seconds provide high velocities and accelerations. M ost of the 
values in the table represent extraordinary velocities and all fall between hypersonic and re-entry 
speed M ach regim es. Acceleration values also show a very high num ber of g.
An exam ination of Table 2 at a At of 5.0 sec reveals the average velocity of the craft was 12,000 
ft/sec (8,182 m ph or M ach 10.7). A very high deceleration value is also witnessed at 2400 ft/sec2 
or 75 g. These are extraordinarily high values and would require som e form of acceleration 
m anipulation to lim it what a hum an pilot would experience and be able to survive.
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Ta ble 2 V elocities a nd  Accelera tions of Tic Ta c for Pa ra metric Time D ura tions of E vent
As 6 0000 feet
As 11.36 36 4 miles
A t (sec) V (ft/s) v (mph) Mach
Number1 a Ift/s1) a(g)
0.0 0 0 0.0 32.2 2 l2
0.5 120,000 81,818 107.5 240,000 7,453
1.0 60,000 40,909 53.7 60,000 1,863
1.5 40,000 27,273 35.8 26,667 828
2.0 30,000 20,455 26.9 15,000 466
2.5 24,000 16,364 21.5 9,600 298
3.0 20,000 13,636 17.9 6,667 207
3.5 17,143 11,688 15.4 4,898 152
4.0 15,000 10,227 13.4 3,750 116
4.5 13,333 9,091 11.9 2,963 92
5.0 12,000 8,182 10.7 2,400 75
5.5 10,909 7,438 9.8 1,983 62
6.0 10,000 6,818 9.0 1,667 52
6.5 9,231 6,294 8.3 1,420 44
7.0 8,571 5,844 7.7 1,224 38
7.5 8,000 5,455 7.2 1,067 33
8.0 7,500 5,114 6.7 938 29
8.5 7,059 4,813 6.3 830 26
9.0 6,667 4,545 6.0 741 23
9.5 6,316 4,306 5.7 665 21
10.0 6,000 4,091 5.4 600 19
; Computed using the speed of sound at sea level under standard conditions 
? Standard acceleration due to gravity
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TicTac Param etric V elocities for Selected Tim es of Event D uration 
(Points are N ot Continuous)
F igure 11. Tic Ta c Pa ra metric V elocities for S elected Times of E vent D ura tion in ft/sec
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Tic Tac Param etric V elocities for Selected Tim es of Event D uration 
(Points are N ot Continuous)
F igure 12. Tic Ta c Pa ra metric V elocities for S elected Times of E vent D ura tion in mph
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TicTac Param etric A ccelerations for Selected Tim es of Event D uration 
(Points are N ot Continuous)
F igure 13. Tic Ta c Pa ra metnc Accelera tions for S elected Times of E vent D ura tion in ft/sec2
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TicTac Param etric A ccelerations for Selected Tim es of Event D uration 
(Points are N ot Continuous)
Time (seconds)
F igure 14. Tic Ta c Pa ra metric Accelera tions for S elected Times of E vent D ura tion in g
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4.1.3 Numerical Analysis of Compressible Flow
C om pressible fluid flow analyses were perform ed to visualize the steady state pressure, 
tem perature and M ach num ber contours around two craft shapes ("Tic Tae" and right circular 
cylinder). The use of com pressible fluid flow and m odeling of air as an ideal gas assum ed the 
aerodynam ics over the craft were not being controlled or m odified through other m eans.
Steady stale solutions for pressure, tem perature and M ach num ber contours around both a 
"Tic Tae" shape and a right circular cylinder were obtained under subsonic, supersonic and 
m ixed conditions. The C FX m odule was capable of solving the three dim ensional unsteady 
N avier-Stokes equations in their conservation form  as shown below in C artesian coordinates in 
the x, y and z directions num erically. For the steady state solutions, the transient term s were 
unchanging and fall out of the equations below.
M omentum:
(& u du du du\ dp (d2u & u d?u\
p{m+u^ + ,Ty + uT!r-fr^{w + w + w)+p9 ’
(dv Ov dv dv\ dp (& v tpv d2v\
pU+“&+''a i/+^r‘^ +''^ +v+^irp’1'
(dw dw dw dw\ dp (& w ^w & w\
p{-5i+u^+"& i+w^)~-d;+,,\^ + w + »e)+pg-
Continuity:
Up d(pu) d(pv) d(pw) _
Ot. di dy dz
Energy:
1 9 Pil
7V?+ 521 + ^1 +— P^Vi
1 Pl*
At +
1 5 P2I
5 V * + ffZi + £2 + ~ P2^2V2A t = 0
where:
A - Area (m )
g gravitational acceleration (9.8 m /s2)
gx - x directional com ponent of gravitational acceleration 
gy - y directional com ponent of gravitational acceleration 
gz - z directional com ponent of gravitational acceleration 
e specific internal energy (J/kg) 
p - density of the fluid (kg/m 3)
p - dynam ic viscosity of the fluid (Pa s)
p - pressure (Pa)
I - tim e (sec)
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u - x velocity (m /s) 
v - y velocity (m /s) 
w ~ z velocity (m /s) 
x - x coordinate 
y - y coordinate 
z - z coordinate
The following sections provide steady state pressure, tem perature and M ach num ber contours 
over the " Tic lac" and right circular cylinder for velocities of 700 m ph and 1500 m ph with an 
environm ental air tem perature of 223 K (-58°F). Attachm ent II and Attachm ent 111 show 
contours for subsonic speeds below 700 m ph and supersonic increm ents between 700 m ph and 
1500 m ph for the "Tic Tac" and a right circular cylinder respectively. A com parison of the 
profiles of the "Tic Tac" geom etry and that of a right circular cylinder was perform ed due to 
other num erous reports of craft with sim ilar capabilities but lacking curvature at the ends of the 
craft. A flat 90° surface m oving through the air would be expected to cause greater resistance 
during flight.
Assumptions:
1. Elevation of 30 ,0 0 0 ft — It was reported by radar observation the object descended from  
approxim ately 60,000 ft to sea level in a m atter of seconds. An average As is com puted by:
s2 - St 60,000ft — Oft
As = ^ =----------------— = 30,000/t
2. Ambient Air Temperature of 223 K (-58F ) ~ An approxim ate am bient environm ental 
tem perature of 223 K was chosen in accordance with an average elevation in the range of 
30,000 ft (which varies with weather conditions) as a starting point for com putational 
investigations.
3. Air M odeled as an Ideal Gas - Air Tem perature, pressure and density are all interdependent 
and are given by the relationship of the ideal gas law:
P M
where:
Ru-G as C onstant (8.314472 m 3Pa K ' m ol ')
M  — M olar M ass (g/m ol)
T - Tem perature (K )
Since the tem perature and density of air decreases with altitude, so does the speed of sound, 
hence a given true velocity results in a higher M ach num ber at higher altitudes. The slice used 
for the contours was taken axially for each geom etric configuration. Reports from aircrew on 
sight indicate the object flew in a horizontal position. A 0° angle of attack was used in all cases 
to try to replicate observed flight conditions.
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9  246 e>0M  
8 5 26 e*004 
7 807e*004 
7 08^*004 
6 36 9 c *- 004 
5 6 4Be>004
S  339 c>005a t j?c uu,<
1 6 -1^*004 .
■2:47^*004 1
[Pa i
F igure 15 Tic Ta c Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 700 mph with M ixed Inlet a nd  
S upersonic Outlet
*004
*004
>004 
2 083**004
t 334c*0D 4 
6 146 t-*D 0: 
-1 C W eH W
2 6 9 9 c >002
2 «5 7e*002
26 16 c*002
2 5 74e>002
2 5 32c*002
2 49 1e*002
[KI
F igure 16 Tic Ta c Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 700 mph with M ixed Inlet a nd  
S upersonic Outlet
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N ovem ber 23, 2010
'age 41


t 35 Be*000 
t 180e*000 
1 101e*000 
1 023e*000 
9  440-001 
8 6 5 4k 001 
7 86 8i-001 
7 09 3 k 001 
6 .29 7e-001 
5  5 11# 001 
4 726 e-001 
3 9 4t>001 
J 1b4i: 001 
2 36 9 e 001 
1 5 83 k 001 
? 9 72e 002 
1 147c-0D 3
F igure 17, Tic Ta c M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 700 mph with M ixed Inlet a nd  
S upersonic Outlet
3 745 c»005  
3 4 9 5 6 *005
3 244c*005  
2 9 9 46 *005
2 704-005
F igure 18. Tic Ta c Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 15 00 mph with S upersonic Inlet a nd  
S upersonic Outlet
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4 39 5 e»002
4 25 3e*002
4,110^*002 
3 9 6 6 e*002
3 B23c*W 2 
3 6 80e*002
3 5 370*002
3 39 3**002
3 25 01002 
J 107**00?
2 9 6 3**002
2 820c*002
2 B77e*D D 2
2 5 34**002
2 39 0c*002 _
2 24 7e 1002 |
2 104**002 " 
M
F igure 19 Tic Ta c Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 15 00 mph with S upersonic Inlet 
a nd S upersonic Outlet
2 29 Ber000 
215 5 e*000 
2011**000 
1.86 8**000 
1 724®*000
1 5 81**000 
1 437e*000 
1 29 4**000 
I 15 0e*000 
t 007**00$ 
8.6 306 *001 
7.19 5 ® 001 
t: 76 0t; 001 
4 325 e 001 
2 89 0* 001 
' 45 5 e U01 
- 017n 003
F igure 20 Tic Ta c M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 15 00 mph with S upersonic Inlet 
a nd S upersonic Outlet
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root* *002 
G84e*002 
6 29 **002 
5 S 3e*002 
5 5 8**002
F igure 21. C ylind er Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 700 mph with M ixed Inlet a nd  
S upersonic Outlet
1 U5 e» 000 
t 06 4**000 
9  9 32c 001 
9  223e-001 
85 13o-001
7 B04r 001
F igure 22, C ylind er M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 700 mph with M ixed Inlet a nd  
S upersonic Outlet
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2 439 **005  
2 26 7**005
2 09 5 **005  
1 9 23**005  
1 75 1c*005
1 5 B0e»0D 5  
1 49 80*005
1 235 e»W 5  
1 06 4O-005  
0 9 23**004 
7 204e»004 
5 4B6 c*004
3 76 Be»004 
2 05 0e*004
3 319 t-O03 
-1 38Ge*-004
3 ->340*004
(Pa )
F igure 23 C ylind er Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 15 00 mph with S upersonic Inlet 
a nd S upersonic Outlet
2 439 e*005  
2 26 7e*005  
2 09 5 **005  
1 9 23e*005
1 75 1c*005
1 5 80e»005
1 408**005  
1 236 **005  
I 06 4e*005  
8 9 23**004
7 2O4e»O04
5 486 **004
3 76 8e«0M  
2 05 0e*004 
3 319 .-003 
1 386 **004
■3 104**004
(Pa )
F igure 24. C ylind er Tempera ture a t 1i6 S ca le, Air Tempera ture 223K a nd 15 00 mph with S upersonic Inlet 
a nd S upersonic Outlet
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217fe»000 
2.0406 *000 
1 9 Q4e*000 
1.76 8e*0M  
1 6 32e*000 
1 4 9 6 6 *000
F igure 25 . C ylind er M a ch Number a t 1/6 S ca le. Air Tempera ture 223K a nd 15 00 mph with S upersonic 
Inlet a nd S upersonic Outlet
4.1.4 Summary anil Conclusions of Compressible Numerical Analyses
In the field of U AP studies, it is believed this prelim inary analysis of the " fie l ac" incident is 
the first of its kind to utilize a m ulti-industry standard FEA code to perform com putational 
studies. The cases used are provided as a basic dem onstration of the C FX fluid flow m odule and 
illustrate sonic of its capabilities, as well as a sam ple of som e visualization tools.
4.1.4.1 "Tic Tae" Geometry
For the contour plots of pressure, tem perature from 100 m ph up to 500 m ph. gradual increases in 
values are observed, with the m ost significant value change at the front of the object. The M ach 
num ber values increase at the front sides of the object. Disturbance of air flow is witnessed in 
the pressure and M ach contour profiles around the body.
N earing the speed of sound al 700 m ph, contours for pressure and M ach num ber started to show 
a m ore pronounced shock as would be expected. Tem perature values also showed a higher 
increase at the front nose due to higher flow and air resistance over the body. Velocities higher 
than 700 m ph showed a drastic difference in values com pared to those at 100 m ph with pressure 
differences in orders of m agnitude. At 1.100 m ph. the tem perature rises not only at the attack 
nose, but started to even increase on the sides and in the wakes of air flow. Detached shock 
waves were witnessed in the pressure and M ach contours starling at 700 m ph all the way up to 
1.500 m ph.
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4,1.4.2 Circular Cylinder Geometry
It would seem  counter intuitive to have a craft with a Hat face pushing through the air due to a 
m ajor increase in air resistance. However, there have been m any reports of objects of just the 
sort seen m aneuvering in the skies. A com parison of the detrim ental aerodynam ic effects was 
sought in relation to the sm oother edged body.
At lower speeds, no large differences in values of pressures, tem peratures or M ach num bers were 
observed. There were, however, slight differences in the location and profiles of the values of 
the "Tic Tac" geom etry com pared to the cylinder. N one of these differences would indicate a 
drastic difference in conventional lift perform ance between the two geom etries. The sam e 
appeared to hold true for higher speed scenarios, indicating no significantly different 
aerodynam ic lift advantages between the two geom etries.
4.1.4.3 Outcome
Success was achieved in im plem enting the AN SYS M ultiphysics and Solid W orks Solid 
m odeling program to create and run input cases for com pressible fluid flow over both 1he 
" Tic Tac" geom etry and that of a right circular cylinder to illustrate pressure, tem perature and 
M ach contour profiles over both shapes. Separated shockwaves were witnessed in higher 
velocity cases indicating that the possibility of a sonic boom or vibration m ay have been 
perturbated into the environm ent. The actual propagation distance of these was not of interest in 
this study and m ay be looked at in the future. It is doubtful the aircrew would have felt a shock 
wave in the cockpit unless extrem ely close to the object while traveling at high rates of speed, 
which the fighter jets were not. These basic geom etries and assum ptions helped provide an 
excellent starling point to create m ore com plex transient cases that possibly incorporate heat 
generation, electrom agnetic effects, and acoustics. This is dem onstrated in a basic m odel that 
FEA algorithm s describing m ultiphysics can provide to he an invaluable tool in gaining insight 
into U AP flight characteristics and even possibly rule out im probable scenarios.
4.1.5 Numerical Analysis of Incompressible Flow of a UAP Entering Water
The problem studied was that of a solid disc shaped object descending through the air into a 
body of liquid. The m odel created, details the descent of a solid disc shaped U AP into water. It 
is assum ed norm al am bient conditions with a solid steel disc m oving at a speed of 5 m /s in the 
negative y (downward) direction. The water surface is approxim ately 10 feet below the bottom  
of (he U AP. W ater and air tem peratures arc held al constant at 25°C and the gravitational 
acceleration constant at 9.81 m /s . Am bient pressure was a constant 1 atm , buoyancy effects 
within the water were accounted for and the U AP was taken to be isotherm al (no heat transfer 
between the system and the surroundings). Three distinct phases were created; a gaseous phase 
(air), the solid phase (U AP) and the liquid phase (water). Figure 26 displays the three 
dim ensional geom etry depicting the distinct regions and boundaries.
The geom etry was com pleted, and the necessary m esh was created in order to carry out the FEA 
analysis. M eshing is the discretization of a continuous dom ain into a set of discrete sub-dom ains 
called elem ents and is shown Figure 27. The governing equations were then solved for all
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elem ents within the dom ain. The accuracy of the solution increases with increasing num ber of 
elem ents (refining of the m esh).
Typically, m eshes are refined near dom ain borders or other places of interest; specifically where 
the solution is desired (for exam ple the edge of solid object where it is desired to determ ine the 
am ount of heat loss from the object). T he solid U AP body was m ore refined than the air and 
water dom ains because it was of prim ary im portance to study fluid ilow around the U AP and not 
the flow of air/watcr further away from  the solid dom ain. A close-up view of the refined m esh in 
the solid U AP dom ain is seen in Figure 28.
Once the m esh was generated, then boundary and initial conditions were assigned to replicate 
approxim ate physical conditions during the event. As the nam e im plies, boundary conditions are 
exact solutions to differential equations that exist on the outskirts of the different geom etries. 
These conditions m ust be m et if the solution is to be correctly determ ined. Initial conditions are 
tim e dependent relationships that describe the initial state of the problem . Therm ophysical data 
m ust be defined for each dom ain. The governing equations include the properties of the m aterials 
involved (cp, p, etc.) and an accurate analysis depends as m uch on the proper accounting of these 
properties as on the proper identification of boundary conditions.
B oundary conditions on the solid U AP edges were set as a no slip surface. A no slip boundary 
sets the fluid velocity at 0. That is to say that a fluid com ing in contact with the surface will not 
m ove (not slip). This is a typical boundary condition used when a fluid com es in contact with a 
solid body. In addition, the outside walls of the boundary were set as no slip. It was assum ed 
that the walls were located far enough away from  the U AP-water im pact zone to play no part in 
determ ination of fluid m ovem ent around the solid U AP body.
Thennophysical data was determ ined by m aterial identification within the problem setup. The 
U AP was defined as being m ade of steel, the liquid body was set as water and the gaseous body 
was set to air. The initial velocity for the U AP was 0 rn/s, that is to say the U AP initially starts al 
rest. Total sim ulation tim e was set to 10 seconds with 0.2 seconds per tim e step (for a total of 50 
tim e steps).
4.1.6 Numerical Analysis of Incompressible Flow of a UAP Entering Water Results
U pon com pletion of the sim ulation; an output file was created and stored for use in the post 
processing portion of W orkbench called C FX-Post. Once the output file has been im ported to 
C FX-Post; a variety of results m ay be obtained. For this investigation, a lluid dynam ic analysis 
was perform ed. To best view the results; a plane (parallel to the y axis) was created to bisect the 
geom etry (see Figure 29).
The creation of a plane contained within the geom etry allows for easy analysis of the solution. 
C FX-Post was used to determ ine the velocities of the air and water lluid dom ain, the pressure of 
the system and through exam ination of the volum e fraction of water; a recreation of the 
appearance of a solid entering the water. An anim ated representation of the transient results was 
created in an effort to understand how the trends in the specified variable change over tim e. 
Figure 30 displays a still im age of an anim ated result showing how the volum e fraction of waler 
changed as the U AP descended into the water dom ain.
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M anipulation of the created plane view allowed for a two dim ensional analysis for a variety of 
param eters. Figure 31 displays a still fram e of the anim ation depicting how pressure varied 
throughout geom etry.
Figure 31 displayed the expected trend of an increasing pressure with increasing depth. A 
rc-crcation of the physical appearance of the U AP im pacting and descending into water m ay be 
achieved through analysis of the transient anim ated results of volum e fraction of water. Figure 
32 displays a still shot of this anim ation after the U AP has im pacted and entered the water 
dom ain.
The radially expanding concentric circles display the resulting ripple effect after the solid has 
penetrated through the surface of the water. Figure 33 displays a side view of the sam e result. 
The original result anim ations from which the still screenshots (Figure 29 through Figure 33) 
were taken are provided in .m peg form . In addition to the preceding results, several anim ations 
depicting transient trends of fluid density and fluid velocity have been provided.
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17 5 00 5 2.5 0
F igure 26 S olid  Three D imensiona l Geometry of D isc a nd W a ter
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F igure 27. S olid Three D imensiona l Geometry M esh of D isc a nd W a ter
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F igure 28. S olid Three D imensiona l Geometry M esh of UAP D isc
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F igure 29 . User Genera ted C ut Ana lysis Pla ne
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6.0 00 6-00 1
5.00 00 -00 1
4.0 00 6-0 01
3.00 0 6-0 0 1
2.00 00 -00 1
1.00 0 e-0 01
1.0 00 6-0 15
8.00 0 e-0 0 1
7.00 0 8-0 0 1
Fluid 2 Volume Fraction
C ontour 1
1—r 1 -OOOe+OOO
9.0 0 0 e00 1
A NM.
F igure 30 Anima ted Result F luid 2 V olume F ra ction
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5 DOG 15 COO
F igure 31. Tota l Pressure Around UAP
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F igure 32 W a ter S urfa ce E ffects F rom S olid Impa ct
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S OW  IS  OTO
F igure 33. W a ter S urfa ce E ffects F rom S olid Impa ct (S id e V iew)
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4.1,7 Summary' and Conclusions of Numerical Analysis of Incompressible Flow of a LAP 
Entering Water Results
The C FX-Post generated graphs and anim ations are illustrative sam ples of what AN SYS C FX is 
capable of producing. The scenario was chosen due to its sim ple geom etry, boundary conditions 
and relative ease of com putational requirem ents. A typical problem  of this type when solved by 
hand, would have taken weeks if not longer. This sim ulation incorporated a fluid dynam ic 
analysis and further analysis m ay incorporate num erous other m ultiphysics attributes in the study 
of U AP. Heat transfer from a craft entering the earth’s atm osphere as well as the effects of 
varying craft size, shape and speed on wave generation during water im pact could be studied just 
as easily. In addition to determ ining power requirem ents, achieved surface tem peratures etc., re­
creations of eyewitness sightings m ay be.
Furtherm ore, electrom agnetic capabilities allow for m odeling of possible m agnetohydrodynam ic 
(M HD) affects. Electrodynam ics can show the energy required to create m agnetic fields with 
different m aterials as well as the propagation of electrom agnetic waves through solid and liquid 
m edium s. U sing careful design and properties of hum an tissue in the program it would be 
possible to show effects on the hum an body from heat and high electric fields. Effects, such as 
increase in body tem perature or nervous system interruption m ay be able to be quantified in 
AN SYS. This tool can greatly assist in the goal of studying hum an effects to reverse engineer 
U AP technology.
4.2 ANALYSES OF SPH ERICAL LAPS
4.2.1 Acoustical Analysis of a Spherical USO
Over the years, there have also been num erous reports U SOs. In 1967, a U FO was reported 
crashing into Shag Harbour, N ova Scotia. It was reported that hovering and flashing orange 
lights were present, then it tilted at about a 45 degree angle and entered the water. A yellow light 
was seen in the water m oving and leaving a trail of yellow foam . The C anadian C oast G uard 
was dispatched but by the tim e they arrived along with other vessels at the point of entry the 
yellow foam  was all that rem ained.
This is one of very few cases where governm ental agency docum ents have form ally declared an 
unidentified flying object was involved. At least eleven people saw a low-flying lit object head 
down towards the harbor. M ultiple witnesses reported hearing a whistling sound "like a bom b," 
then a "whoosh," and finally a loud bang. Som e reported a flash of light as the object entered the 
water. Several interviewed m ilitary witnesses, including a diver involved in an attem pted 
recovery, have claim ed an alien spacecraft was responsible. It was also claim ed by several of the 
witnesses that the U .S, m ilitary was involved in recovery attem pts. The case was also briefly 
investigated by the 1843(a)(2) U FO study, which offered no explanation.
It has been proposed that this type of craft m ay operate using som e sort of electrom agnetic 
frequency based propulsion system to control underwater "flight" and to achieve incredible 
perform ance capabilities in velocity and acceleration.
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The three-dim ensional acoustic wave equation is given below in the second order partial 
differential equation:
d2p d2p d2p 1 d2p—- + —- + —--------- — = 0dx2 dy2 dz2 c2 dt2
and
where
B b - adiabatic bulk m odulus (Pa) 
c - speed of sound in m edium  (m /s) 
p - pressure (Pa) 
t-tim e (sec) 
p - density of m edium  (kg/tn ) 
x - x coordinate 
y - y coordinate 
z - z coordinate
The following solutions arc obtained by separation of variables in different coordinate system s. 
Phasor solutions result, (hat is they have an im plicit tim e-dependence factor of e1^ where 
to ~ 2k(is the angular frequency. The explicit tim e dependence is given by:
p(r,t,k) = Real [pfr,*:)^]
Here fc = ^ is the wave num ber and r is the displacem ent vector.
In C artesian coordinates and C ylindrical coordinates respectively: 
p(r,i) = ^ 
p{r^^Al^\^y BH^kr)
where the asym ptotic approxim ations to the Hanke! functions, when kr - ♦ oo, are
H^\kr) -
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and in Spherical coordinates:
Depending on the chosen Fourier convention, one of these represents an outward traveling wave 
(real) and the other an unphysical inward travelling wave (im aginary).
Assum ing U SOs operate on a frequency driven system , an AN SYS M ultiphysics 1/100,h scale % 
sym m etry Acoustical full harm onic analyses was perfonned to study a spherical object of 10 in 
in both air and water for a range of frequencies at standard conditions. Provided below are 
contour plots for the real, im aginary and m agnitude com ponents of pressure and plots for 
pressure as a function of radius in Pa.
Ta ble 3. Properties of W a ter Used  for ANS YS  H a rmonic Ana lyses
Property Value
W a ter D ensity 1,000 kg/n?
S peed of S ound 1,5 00 m/s
Reference Pressure 1 * 10‘6 Pa
Figure 34 and Figure 35 show the FEA m esh for 25 elem ents per wavelength and 50 elem ents 
per wavelength for a 1,000 Ik analysis. U pon inspection of the m axim um pressures shown in 
Figure 36 and Figure 37, it is apparent the FEA m odel solution was m esh independent with a 
pressure of 1,052 Pa for the 25 elem ent per wavelength m odel and 1,103 Pa for the 50 elem ent 
per wavelength m odel. G enerally higher elem ent m odels for m eshes are considered m ore 
accurate, but a cost in com putational tim e m ay be seen in extrem ely large m odels. In the runs 
perform ed, the 25 elem ent per wavelength m odel showed sufficient accuracy and reasonable 
com putation tim es. As frequency was adjusted higher, the elem ents per wavelength were 
adjusted down to lim it elem ent num bers.
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F igure 34 M esh Plot for 1,000 H z with 25 E lements per W a velength in W a ter
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U niform ly Radi a Ling Sphere, EF>b50
F igure 35 . M esh Plot for 1,000 H z with 5 0 E lements per W a velength in W a ter
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F igure 36 . C ontour Plot of Rea l C omponent of Pressure (Pa ) for 1,000 H z with 5 0 E lements per W a velength in W a ter
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F igure 37. C ontour Plot of Rea l C omponent of Pressure (Pa ) for 1,000 H z with 5 0 E lements per W a velength in W a ter
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F igure 33, C ontour Plot of Ima gina ry C omponent of Pressure (Pa ) for 1.000 H z with 25 E lements per W a velength in W a ter
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F igure 39 . C ontour Plot of the M a gnitud e of Pressure (Pa ) for 1.000 H z with 25 E lements per W a velength in W a ter
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F igure 40. S tea d y S ta te Rea l C omponent of Pressure (Pa ) a s a F unction of Ra d ia l D ista nce (m) Plot for 1.000 H z with 25 E lements per 
W a velength in W a ter
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F igure 41 S tea d y S ta te Ima gina ry C omponent of Pressure (Pa ) a s a F unction of Ra d ia l D ista nce (m) Plot for 1.000 H z with 25 E lements per 
W a velength in W a ter
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F igure 42. S tea d y S ta te M a gnitud e of Pressure (Pa ) a s a F unction of Ra d ia l D ista nce (m) Plot for 1,000 H z with 25 E lements per W a velength in 
W a ter
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uniform ly Rxiijtiix; Sphere, EE?K 5
F igure 43. C ontour Plot of Rea l C omponent of Pressure (Pa ) for 5 .000 H z with 25 E lements per W a velength in W a ter
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F igure 44. C ontour Plot of Ima gina ry C omponent of Pressure (Pa ) for 5 .000 H z with 25 E lements per W a velength in W a ter
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F igure 45 . C ontour Plot of the M a gnitud e of Pressure (Pa ) for 5 ,000 H z with 25 E lements per W a velength in W a ter
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F igure 46 . S tea d y S ta te Rea l C omponent of Pressure (Pa ) a s a F unction of Ra d ia l D ista nce (m) Plot for 5 ,000 H z with 25 E lements per 
W a velength in W a ter
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F igure 47. S tea d y S ta te Ima gina ry C omponent of Pressure (Pa ) a s a F unction of Ra d ia l D ista nce (m) Plot for 5 ,000 H z with 25 E lements per 
W a velength in W a ter
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F igure 48. S tea d y S ta te M a gnitud e of Pressure (Pa ) a s a F unction of Ra d ia l D ista nce (m) Plot for 5 ,000 H z with 25 E lements per W a velength in 
W a ter
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F igure 49 . C ontour Plot of Rea l C omponent of Pressure (Pa ) for 10.000 H z with 25 E lements per W a velength in W a ter
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F igure 5 0. C ontour Plot of Ima gina ry C omponent of Pressure (Pa ) for 10,000 H z with 25 E lements per W a velength in W a ter
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F igure 5 1 C ontour Plot of the M a gnitud e of Pressure (Pa ) for 10.000 H z with 25 E lements per W a velength in W a ter
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F igure 5 2. S tea d y S ta te Rea l C omponent of Pressure (Pa ) a s a F unction of Ra d ia l D ista nce (m) Plot for 10.000 H z with 25 E lements per 
W a velength in W a ter
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F igure 5 3 S tea d y S ta te Ima gina ry C omponent of Pressure (Pa ) a s a F unction of Ra d ia l D ista nce (m) Plot for 10,000 H z with 25 E lements per 
W a velength in W a ter
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F igure 5 4. S tea d y S ta te M a gnitud e of Pressure (Pa ) a s a F unction of Ra d ia l D ista nce (m) Plotfor 10,000 H z with 25 E lements per W a velength in 
W a ter
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4.2.1.1 Summary and Conclusions of Acoustic Analyses
A successful analysis of a U SO was conducted using a full harm onic acoustics sim ulation. The 
plots of the real and im aginary values showed good agreem ent with the expected theoretical 
solutions. It m ay be concluded from the contour plots and graphs that the varying frequencies 
produce acoustics pressures far out from the actual source and decline in an inverse square law 
relationship. In the future, ships and subm arines could possibly detect these pressure 
disturbances and a frequency of the m ode of operation could be calculated with a known distance 
from  the vessel.
4,2.2 ANSVS Multiphysics Electromagnetic Capabilities
The electrom agnetic capabilities of AN SYS M ultiphysics include a full-wave electrom agnetic 
solver applicable to resonant, propagating, radiation and scattering phenom ena iii the frequency 
dom ain. RF or m icrowave passive com ponents, antennas, attenuators, interconnects and related 
high frequency structures m ay be m odeled for use in applications of stealth, electronic warfare 
and directed high energy applications. Post-processing calculations provide electric and 
m agnetic field intensity, quality factor, scattering m atrix param eters, voltage, current, 
characteristic im pedance, radar cross section, far and near electrom agnetic fields beyond the 
m odeled dom ain, antenna patterns, including period structures, and Joule losses (AN SYS, Inc., 
2009). M agnetohydrodynam ics m ay also be m odeled in developm ent of propulsion units and 
power generation, electron beam dynam ics and electrical discharges. The M axwell Equations 
below provide the basis for electrom agnetic calculations.
V -D  = pe
dD
VB  = 0 
where:
B - m agnetic induction field (tesla)
D - displacem ent field (C /m 3)
E - electric field (V/m )
H - m agnetic field (A/m )
J — current density 
pc - charge density
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4.2.3 Radar Cross Section Analysis of a Spherical UFO
M any U AP have been reported across the globe. Pilots have reported seeing these craft in the 
air. but when asked for confirm ation of other aircraft in the area, air traffic control reports 
nothing on radar.
Only a tiny fraction of energy is bounced back to the receiving antenna, even though m any 
m egawatts of power m ay be transm itted in a single pulse. The am ount of power returned from a 
target to the transm itting radar depends on four m ajor factors:
1. The power transm itted in the direction of the target.
2. I he am ount of power that im pacts the target and is reflected back in the direction of the 
antenna. This is directly relational to the range between the antenna and target and the 
target’s RC S.
3. The am ount of reflected power that is received by the antenna.
4, The length of tim e in which the antenna is pointed at the target.
P«wt c< W a ves
F igure 5 5 . F a ctors tha t D etermine the E nergy Returned by a  Ta rget (Aerospa ceweb.org ,2010)
Power flux is used to describe the relationship between these variables. The further the radar 
wave travels, the greater the power transm itted decrease because it is spread over a larger area. 
The inverse square law of the range R or I/l<‘ governs the area over which the power is spread 
from the transm itting radar. The power flux or power density of the transm itted radar wave al 
the range of the target has a special nam e called the incident power density (Pim idcm )*
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Power reflected back to 
the radar depends on the 
power Intercepted by the target 
and the target orientation
F igure 5 6 . E ffect of D ista nce from the ra d a r to the Ta rget on the Power D ensity (Aerospa ceweb.org , 
2010)
W hen the radar wave reaches the target, a portion is reflected back to the antenna, In addition, 
the reflected power also dissipates at 1/R2 therefore it is reduced by a factor of PR1 roundtrip by 
the tim e it is returned to the antenna. The ability of a radar system  to detect a target depends on 
whether the am ount of power relum ed is great enough to be differentiated from internal noise, 
ground clutter, background radiation, and other sources of interference. This is defined as the 
signal to noise ratio. The object of stealth is to absorb or reflect waves away from receiving 
antenna and/or jam or propagate a false wave back to its source so that the target is nearly 
im possible to detect or track.
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The am ount of power that is reflected back to the radar depends largely on a quantity called the 
radar cross section (RC S). RC S (a) is technically an area and typically expressed in square 
m eters (m 2) and depends on the following three factors:
Geometric cross section:
The area of the object presented to the antenna or projected area is known as the geom etric cross 
section. The area varies depending on the angle, or aspect, seen by the radar. The geom etric 
cross section (A) determ ines how m uch power transm itted by the radar (Pincident) is intercepted by 
the target (Pinterccptcd) according to the following equation:
^intercepted —  A  P incident
Reflectivity:
The reflectivity is the fraction of the intercepted power that is reflected by the target, regardless 
of direction. An object doesn’t always reflect equally from  all directions as som e parts are flat or 
curved producing varying radar reflection and som e of the power is absorbed by the object. 
Objects that have radar Absorbent M aterials (RAM ) and radar Absorbent Structures (RAS) are 
designed using internal reflectors to trap incom ing radar waves. The power received by the 
antenna after scattering or reflecting off the target is equal to the intercepted power less whatever 
portion of that power is absorbed by the target. The reflectivity is the ratio of power scattered by 
the target (P5C B tt«) to the power intercepted by the target (Pintercepted).
Reflectivity =  scatter—
^'intercepted
D irectivity:
The directivity is related to reflectivity but refers to the power scattered back in the direction of 
the receiving antenna. The power that is reflected toward the antenna is called the backscallered 
power (Pbackscaner)- Directivity is the ratio of the power that is backscattered in the direction of 
the antenna to the power that would have been scattered in that direction if the scattering were in 
fact uniform  in all directions. Isotropic power (Pbotropic) is the power scattered in a perfect sphere 
over a unit solid angle of that sphere.
.. .. P ftackscatter P backscatter 
D irectivity = — -----------= — :-------------
•isotropic —L p
4tt rscatter
The reflected power will be m uch greater or m uch sm aller than the isotropic power depending on 
how the target is oriented to the transm itting antenna. The directivity, therefore, will be m uch 
greater than J when the target returns a strong backscatter in the direction of the receiving 
antenna and m uch less than 1 when the backscatter is sm all.
These three factors can be com bined to determ ine the com plete RC S (o) for a target.
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RCS = ct = Geometric Cross Section x Reflectivity x D irectivity
, ^backscatter
C T = 47T—---------
r intercepted
The im portance of RC S can best be understood by looking at an equation relating the RC S of the 
target to the energy received by the antenna.
„ ~ ^vg^^^e^ot 
= (47r)2R*
where
S = signal energy received by the radar
Pavg = average power transm itted by the radar
G ~ gain of the radar antenna
ct = RC S
Ae - effective area of the radar antenna, or "aperture efficiency" 
t01 = tim e the radar antenna is pointed at the target (tim e on target) 
R - range to the target
Figure 57 shows a target that presents the sam e aspect to the radar at ranges from 1 to 50 m iles. 
At a range of 50 m iles, the relative power received by the radar is only 0.00000016, or 
1.6 x IO7 % of the strength at one m ile. This diagram graphically illustrates how significant the 
effect of energy dissipation is with distance, and how sensitive radars m ust be to detect targets at 
even short ranges.
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F igure 5 7. Red uction in the S trength of Ta rget E choes with Ra nge (Aerospa ceweb org , 2010)
Furtherm ore, every radar system has a m inim um signal energy it can detect, a quantity called 
Sm in. This m inim um signal energy along with antenna design and scan rate determ ine the 
m axim um  range (R^ax) at which a given radar can delect a given target.
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F igure 5 8 Geometry. D escription a nd M a ximum RC S (Aerospa ceweb.org , 2010)
Geometry Description Maximum 
RCS Comments
S qua re 
trihed ra l corner 
reflector
12m a4
" X2
S trongest ra d a r return d ue to 
triple reflection of incid ent wa ve
Right d ihed ra l 
corner reflector
8m a2b2CT —
S econd strongest ra d a r return 
d ue to d ouble reflection of 
incid ent wa ve; d ecrea ses from 
ma ximum slowly with cha nging 0 
a nd ra pid ly with cha nging <p
X2
F la t pla te 4m a2b2CT “
Third strongest ra d a r return d ue 
to d irect reflection of incid ent 
wa ve; d ecrea ses ra pid ly a s 
incid ence a ngle cha nges from 
perpend icula r
1*
X2
b \^5
Right circula r 
cylind er
2m a b2 a=---------- X
S trong ra d a r return a s a spect (9 ) 
cha nges, but d ecrea ses ra pid ly 
a s a zimuth (<p) cha nges
S phere o = m a2 Prod uces the sa me isotropic 
return in a ll d irections
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RC S in square m eters can be converted to dB sm  by the following equation.
dBsm = 10 Log(RCSm2)
It can be difficult to directly com pare RC S estim ates from one object to another since the RC S 
varies wildly depending on aspect, radar frequency and wavelength, and the fidelity of the 
receiver. Figure 59 illustrates typical RC S values for aircraft and other objects, ranging from  
insects and birds up to large ground vehicles and ships. The RC S of a stealth aircraft is typically 
m ultiple orders of m agnitude lower than a conventional plane and is often com parable to that of 
a sm all bird or large insect.
Comparison of Typical Radar Cross Sections in Square Meters
.0 00 1 JM1 411 ,1 1 10  10 0 1.0 0 0 10 ^)0 0  10 0 ,00 0
H -----1-----1-----1-----1----1-----1-----1-----1-----1-----1-
INSECTS BIRDS Mi LIGHT GROUND VEHICLE
■ TA NK , A RMORED VEHICLE
MS SURFA CE SUP
■■■BOMBER
y FIGHTER MB A IRCRA FT CA RRIERBand
CRUISE MISSILE
F igure 5 9 . Ra d a r C ross S ection C ompa rison (Aerospa ceweb.org , 2010)
A one-half sym m etry analysis of the radar cross section of a U AP sphere with a dielectric 
coaling was perform ed. Assum ing the bottom lim it of an ullrahigh frequency (U HF) very long 
range radar system  is 300 M Hz, a full scale RC S full harm onic analysis was perform ed to study a 
spherical object of 10 m in air with a 1 m dielectric coating layer. Provided in Figure 64 is a 
contour plot for the electric field distribution.
Figure 60 and Figure 61 show the FEA m esh for 25 elem ents per wavelength and 50 elem ents 
per wavelength for a 300 M Hz RC S analysis.
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F igure 6 0. M esh of 'A S ymmetry UF O S phere with 25 E lements per W a velength
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F igure 6 1 M esh of 7? S ymmetry UF O S phere with 5 0 E lements per W a velength
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Ta ble 4 Norma lized ra d a r C ross S ection for a 10 m M eta llic S phere with a lm D ielectric C oa ting in
D ecibels for 300 M H z a nd  25 E lements per W a velength
PHI (Deg) THETA (Deg) Normalized RCS (dB)
0.000 0.000 -0.1746 1E +01
0.000 5 .000 -0.1839 6 E +0I
0. 000 10 000 -0 2089 1E *01
0.000 15 .000 -0 2405 9 E +01
0.000 20 000 -0 26 3O6 E +O1
0 000 25 000 -0 25 6 83E +01
0 000 30.000 -0 2105 6 E +01
0 000 35 .000 -0. 1309 0E *0l
0. 000 40.000 -0.36 5 28E +OO
0. 000 45 .000 0.5 45 01E +00
0.000 5 0.000 0 13011E +01
0.000 5 5 .000 0 18315 E +01
0.000 6 0 000 0 20883E +01
0. 000 6 5 000 0 2O27OE +O1
0 000 70 000 0 I5 9 03E +01
0.000 75 .000 0. 6 9 09 5 E +OO
0 000 80 000 -0 8I414E +OO
0.000 85 .000 -0.315 41E +01
0.000 9 0.000 -0 6 4801E +01
0.000 9 5 .000 -0.85 723E +01
0. 000 100.000 -0.5 426 2E +O1
0.000 105 . 000 -0 16 5 86 E +01
0.000 110.000 0 10839 5 *01
0.000 115 .000 0.29 9 83E *01
0 000 120 000 0 43027E +01
0 000 125 .000 0.5 1444E +01
0.000 130.000 0.5 6 415 E +01
0 000 135 .000 O.5 9 2O2E +OI
0.000 140 000 0 6 1375 E +O1
0.000 145 .000 0 6 46 6 2E *01
0.000 15 0.000 0 7O226 E *O1
0.000 15 5 .000 0.779 2 IE *01
0.000 16 0.000 0. 86 49 3E *01
0. 000 16 5 000 0 9 4471E *O1
0.000 170.000 0 10076 E *02
0 000 175 000 0 10474E +02
0.000 180.000 0 106 09 E +02
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F igure 6 2. Norma lized ra d a r C ross S ection Plot for a %  S ymmetry 10 m M eta llic S phere with a lm D ielectric C oa ting in D ecibels for 300 M H z 
a nd 25 E lements per W a velength
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Ta ble 5 . Norma lized ra d a r C ross S ection for a 10 m M eta llic S phere with a 1 m D ielectric C oa ting in
D ecibels for 300 M H z a nd 5 0 E lements per W a velength
PHI (Deg) THETA (Deg) Normalized ROS (dB)
0.000 0.000 -0.I3803E +0I
0.000 5 .000 -0. 145 03E *01
0.000 10.000 -0.16 341E +01
0 000 15 .000 -0.185 35 6 +01
0 000 20 000 -0.19 8O7E +O1
0 000 25 000 -0.18742E +O1
0 000 30.000 -0.145 9 2E +O1
0 000 35 .000 -0. 785 O2E +OO
0 000 40 000 0 I1714E -O1
0.000 45 .000 0.78777E +OO
0.000 5 0 000 0 I436 0E +OI
0.000 5 5 .000 0. I8849 E +0I
0.000 6 0 000 0 2082IE *01
0.000 6 5 .000 0 l9 780E‘0l
0 000 70 000 0 I5 1O9 F ‘O1
0 000 75 000 0 5 89 74E +OO
0 000 80 000 -0 9 325 0E +00
0 000 85 .000 -0. 329 02E +01
0.000 9 0.000 -0 6 6 39 0E +01
0.000 9 5 000 -0. 87O47E‘OI
0.000 100 000 0 5 4874E +01
0 000 105 000 -0.17O16 E +O1
0 000 110 OOO 0.10488E +01
0 000 115 000 0 29 7OOE +O1
0 000 120 000 0 42801E +01
0 000 125 000 0 5 1239 E +01
0 000 130 000 0 5 6 15 9 E +01
0 000 135 000 0. 5 8773E +01
0.000 140.000 0 6 06 086 *01
0.000 145 .000 0 6 3411E +01
0.000 15 0 000 0. 6 846 4E +01
0.000 15 5 000 0. 75 76 9 E +0I
0 000 16 0 000 0 841?5 F ’01
0 000 16 5 000 0 9 2021E +01
0 000 170 000 0 9 8300E +01
0.000 175 .000 0. I0228E +02
0.000 180.000 0 I036 4E +02
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F igure 6 3 Norma lized ra d a r C ross S ection Plot for a %  S ymmetry 10 m M eta llic S phere with a lm D ielectric C oa ting in D ecibels for 300 M H z 
a nd 5 0 E lements per W a velength
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F igure 6 4. E lectric F iled C ontour in V /m for a >4 S ymmetry 10 m M eta llic S phere with a 1 m D ielectric C oa ting in D ecibels for 300 M H z a nd 25
E lements per W a velength
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4.2.3.1 Summary and Conclusions of RCS Analysis
A successful analysis of a spherical U AP RC S was conducted using a full harm onic 
electrom agnetic sim ulation. U pon inspection of the values of norm alized RC S at 90°, the dll 
shown in fable 4 and 'fable 5, it is apparent the FEA m odel solution was m esh independent with 
a pressure of -0.64801 E+01 dB for the 25 elem ent per wavelength m odel and -0.66390E+01 dB  
for the 50 elem ent per wavelength m odel. In the runs perform ed, the 25 elem ent per wavelength 
m odel showed sufficient accuracy and reasonable com putation tim es, The norm alized RC S plots 
and electric field contour illustrate the variation of RC S dB and V/m  values over a range of 0 to 
180°. As one would expect, the values are largest at the point of incident of the radar wave and 
som e reflection and also decrease in m agnitude were witnessed around (he sphere. Various 
shapes of U APs m ay be evaluated for RC S and the resulting electric field due to an incidental 
radar wave is also attainable. This inform ation m ay be used in the future for cases reported to 
determ ine the prom inence of an object’s expected RC S and whether sim ilar radar returns were 
received.
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5. SUMMARY AND CONCLUSION
C om pressible and incom pressible fluid flow, dynam ics, acoustics and radar theory all were 
provided in this report to give the reader a brief overview and understanding of the num erous 
physical equations that m ay be applied to reported U AP and U SO behavior. N um erical solutions 
to these partial differential equation system s (m any of which do not posses analytical or closed 
form  solutions) which describe the physics of the event are achieved with m illions of elem ents to 
m odel the object dom ain and m edium . Each clem ent m ay have num erous sets of coupled 
physical equations that need be solved by passing through m any different com putational 
iterations until convergence is achieved. B AASS is one of the few com panies possessing the 
expertise, com puter software and com putational platform s to achieve such sophistication in 
num erical studies of U AP,
C om pressible fluid flow analyses were perform ed to calculate and visualize the steady state 
pressure, tem perature and M ach num ber contours around two non-conventional craft shapes. A 
solid disc shaped object descending through the air into a body of liquid was investigated to 
provide visual sim ulation of the disturbance produced on the surface of the water through use of 
incom pressible fluid flow. The U SO analyses were perform ed using a full harm onic acoustics 
sim ulation and a spherical U AP RC S m odel was com pleted using a full harm onic 
electrom agnetic sim ulation. Tor the individual sum m ary and conclusions of each analytical and 
num erical study, see Sections 4.1.2,4.1.4, 4.1.7, 4.2.1.1, and 4.2.3.1 of this report.
From  a m ore general perspective, B AASS was created in 2008 in order to facilitate the long term  
research and developm ent of novel and em erging future technologies worldwide as they 
specifically relate to air and spacecraft. A large com ponent of the B AASS m ission is to study in 
depth the perform ance characteristics of U AP and U SOs. From the data accrued, it is also 
B AASS’s m ission to produce a Threat Assessm ent of U AP and U SO perform ance and 
capabilities. As a first step in accom plishing (his m ission B AASS has 1) acquired significant 
field data collection capabilities, both hum an and instrum ented, 2) built the largest known U AP 
perform ance and behavior Data W arehouse in the world and 3) acquired advanced com putational 
ability to analyze the data accrued,
Research and developm ent necessary for the procurem ent of the technology required for 
advanced space and weapons system s arc conducted through use of com putational M ultiphysics 
FEA, developm ent of com puter code, experim entation, m aterial science testing and 
m anufacturing of prototypes in both B AASS in-house and collaborating facilities and 
laboratories. Academ ic areas of concentration include C om putational Fluid Dynam ics (C FD), 
Heat Transfer, N uclear Engineering, Electrom agnetics and Radio Frequencies (RF), Theoretical 
and C om putational Physics, B iological Sciences and C hem istry.
Theoretical and com putational applications, as well as experim entation on com ponents of 
non-conventional propulsion system s is under way to provide for future developm ent of vehicles 
that are capable of operating in the atm osphere, under waler and in space. Operation of the 
vehicle in different m edium s, as well as a goal of hypersonic flight would provide superior 
perform ance in its ability to reach intended targets, faster delivery of weapons, greater effective
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range and an engagem ent capability enabling em ploym ent of com plex tactics against m ultiple 
targets across m ultiple dom ains. 'Ibis research intends to provide innovative approaches and 
concepts for aircraft, propulsion, and flight technologies that dem onstrate significant advances in 
perform ance and capabilities beyond those in operation today.
This report outlined software, equipm ent and database descriptions along with select theory, 
analytical and num erical solutions for U AP incidents through engineering and physics analyses. 
M any analyses of U AP m ay use analytical or closed form solutions to solve the equations that 
describe the physics of an event. W here analytical solutions do not exist or the geom etry is too 
com plex, B AASS incorporates AN SYS M ultiphysics to provide a powerful com putational 
platform to solve large problem s num erically, while com bining and solving m any different 
physical equations. The com bination of com putational software with field m easurem ent 
equipm ent and historical databases of U AP events allows B AASS to utilize state of the art 
engineering techniques and tools to assess the operational capabilities of U AP and U SOs. A 
greater understanding of these objects will allow for an accurate threat assessm ent, as well as 
provide the physics behind the incredible perform ance attributes that som e have displayed. 
B AASS’ acquired knowledge and capabilities are leading the way to quantum leaps in 
technology for travel in the atm osphere, space and under water, along with advances in 
arm am ent and defense system s.
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1843(a )(2)
6. REFERENCES
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1843(a )(2)
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SYMBOLS AND ACRONYMS 
A - Area
AAV - anom alous aerial vehicle
A« - effective area of the radar antenna, or "aperture efficiency" 
B m agnetic induction field
B AASS - B igelow Aerospace Advanced Space Studies 
B a - adiabatic bulk m odulus 
c - speed of sound in m edium  
C FD - com putational fluid dynam ics 
C SG  - C arrier Strike G roup 
D - displacem ent field
DIA - Defense Intelligence Agency 
E - electric field
FEA - Finite Elem ent Analysis 
FLIR - forward looking infrared 
fluid structure interaction 
g - gravitational acceleration 
G  - gain of the radar antenna 
G B - gigabyte 
gx - x directional com ponent of gravitational acceleration 
gy-y directional com ponent of gravitational acceleration 
gz - z directional com ponent of gravitational acceleration 
11 - m agnetic field
IIDV - High Definition Video 
J - current density 
k - wave num ber
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M  - m olar m ass
M HD - m agnetohydrodynam ics
p - pressure
Pavg - average power transm itted by the radar
Pbackscatter - backscattered power
Pincident - incident power density
Pimercepted - power intercepted by the target
Pisoiropic - isotropic power
Pfatter - power scattered by the target
R - range to the target
Rmax - m axim um  range
Ru - gas constant
radar - radio detection and ranging
RC S - radar cross section
RF - radio frequency
S - signal energy received by the radar
Smin - m inim um  signal energy
T - tem perature
I B - terabyte
t — lim e
tot= tim e the radar antenna is pointed at the target (tim e on target) 
u - x velocity
v - y velocity
w - z velocity
x - x coordinate
y - y coordinate
z - z coordinate
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U AP - unidentified aerial phenom ena 
U AV - unm anned aerial vehicle 
U FO - unidentified Hying object 
U I IF - ultra high frequency
U SO - unidentified subm erged object 
e - specific interna] energy 
p - dynam ic viscosity of the fluid 
p - density of the fluid 
pc - charge density 
ct - radar cross section 
co angular frequency
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ATTACH MENT 1 - ANSYS INPUT FILES
USO ANSYS Multiphysics Acoustics Input File Example
! 1/1 OOth Acoustical M odel of a 10 m  Spherical U SO in W ater
I at 1000 Hz 
i.................................................................................
r_________________________________________
! Define variables for problem :
1 Radiating Sphere of Radius SPIIRRADS with uniform  surface 
! velocity of VELOC ITY oscillating at FREQU EN C  
!_________________________________________
♦set,FREQU EN C ,1000
* set,VELOC ITY,0.005
* set,Pl ,acos(-l)
*set,SPHRRADS,0.1
♦set,TOLER,0.0001
i________________________________________________
! Fluid properties:
! Density, Speed of sound in water, Reference pressure
♦set, W ATRDEN S, 1000 
*set,W ATRSON C ,1500
*set,REFEPRES,lE-6
i.................................................................................
1 G eom etry info
! Infinite radius at IN FIRADS m eters
! IN FIXOFF, IN FIYOFF not used right now... 
i_________________________________________
*set,IN FIRADS,5
♦set,IN FIXOFF,0.0
♦set,IN FIYOFF,0.0
i________________________________________________
! M esh info
! U se m apped m esh? YES=1 N O-O (use N O for now)
! Elem ents per wavelength (EPW )
i________________________________________________
*set,M APDM ESH,0
*set,TRlM ESII,l
♦set,EPW ,50
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! G raphics settings
! Set title and subtitles
1 M ake sure the legend is always on (/plopt,info,on)
1 Put global triad al right top corner (Zlriad.rtop)
! Turn on Full G raphics because of DDTSREP# 16215
|_________________________________________
/title,U niform ly Radiating Sphere, EPW =%EPW %
/stitle,l,Sphere radius of %SPHRRADS%m
/stitie,2,Frequency at %FREQUEN C %IIz
/stitle,3,U niform  velocity of %VELOC ITY%m /s
/stitlc,4,Infinite B oundary of %IN FIRADS%m  al (%IN FIXOFF%,%IN FIYOFF%)
/plopt,info,on
/triad,rlop
/graphics,full
! Enter Preprocessor
/prcp7
1 Define elem ents
I 1 = fluid w/ structure
! 2 = fluid no structure
I 3 = infinite fluid
! Define elem ents and keyopts (et) (keyopt)
! Define real constants (r)
1 Define m aterial properties (m p)
et,l,fluid29
keyopt, 1,2,0
keyopt, 1,3,1
et,2,fluid29
keyopt,2,2,1
keyopt,2,3,1
et,3,fluidl29
keyopt,3,3,1
r,l,REFEPRES
r,2,REFEPRES 
r,3,IN FIRADS,0,0,
m p,dens,l,W ATRDEN S
m p,sonc,l,W ATRSON C
m p,dens,2,W ATRDEN S
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m p,sonc,2,W ATRSON C
m p,sonc,3,W ATRSON C  
r.................................................................................. 
! C reate geom etry
! C reate five 90 degree quarter circles (pcirc)
! M erge keypoints (num m rg,kp)
I________________________________________________
pcirc, 1,SPHRRADS, 0,90,
pcirc,2,1,0,90,
pcirc,3,2,0,90,
pcirc,4,3,0,90,
pcirc,5,4,0,90,
num m rg,kp
! M esh
! Set global elem ent size based on EPW above
! M ap with quads, quad-dom inant for free m esh (m shape,0)
! M esh m apped or free (m shkey)
! Set area attributes (aatl)
! M esh all areas (am esh)
! Set plot controls based on clem ent type num ber
esize,(W ATRSON C /FREQU EN C )/EPW
m shape,TRIM ESH
m shkey,M APDM ESH
aatt,2,2,2
am esh,all
/pnum ,1ype,l
/num ,l
/auto
eplot
|__________________________ ______________
! Rotate all nodes in cylindrical C S
...................................................................
csys,l
nrotate,all
!.................................................................................
1 C hange elem ents near center to fluid with struct present
!_________________________________________
typed
real,!
m at,!
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nsel,s,loc,x,SPHRRADS
esln
nsle
em odi fall
t................................................................................
! Apply struct boundary conditions on elem ent type 1
I C onstrain all translation DOF (the '’free" DOF)
! Reapply velocity as displacem ent on inner nodes in radial
! dir. (ux)
I Apply FS1 (fluid-struct interface) flag to active
I_________________________________________
d.all.uy
d.all,ux
nscl,s,loc,x,SPU RRADS
d,all,ux,0,-VELOC ITY/(2*PI*FREQUEN C )
sf.all,fsi
M esh Infinite fluid dom ain
Instead of m eshing, use ESU RF to generate elem ents on ! existing m esh
type,3
real,3
m at, 3
esefall
nscLsdoc.xJN FlRADS.IN FIRADS H OLER
esurf,al I
allsel,all
finish
solution options
Full harm onic analysis 
frequency at FREQUEN C  
select everything & solve
/solu 
antype,harm  
hropt,full 
hrout,on 
lum pm ,0 
eqslv.sparse 
harfrq,FREQU EN C  
nsubst,
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N ovem ber 23, 2010
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kbc.O
al befall
solve
finish
I................................................................................................
! postprocessing w/ annotations
! Load real (set, 1,1,1,0) and plot pressure
I Load im ag (set, 1,1,1,1) and plot pressure
! do a load case com b, to SRSS for pressure m agnitude
[_________________________________________
/postl
/tsp„0.75
/ana,dele
/tla,-.90,.90,Plot of real part of pressure
/dscale,l,off
set,1,1,1,0
pinsol. pres
/tsp„0.75
/arm ,dele
/tla,-.90,.90,Plot of im ag part of pressure
set, 1,1,1,1
/rcplot
/tsp„0.75
/ann,dele
/tla,-.90,.90,Plot of m agnitude of pressure
lcdef,l,l.l,0
luoper,srss, 1
/rep lot
!..................................................................................
! path operations 
!..................................................................................
csys,0
lsel,s,loe,x,0
nsll,s,l
*get,N C OU N T,node„count
csys,l
nsel,s,loc,x,SPI IRRADS
nsel,r,loc,y,90,90+TOLER
SIRTN ODEndnext/O)
nsel,s,loc,x,lN F]RADS,IN FIRADS+TOLER
nsel,r,loc,y,90,90+TOLER
FIN IN ODE=ndnext(0)
Sum m ary Report on B AASS U AP Analysis C apabilities
N ovem ber 23, 2010
Page 109


allsel,all
path,RADIAL,2,30,(N C OU N T-1)
ppalh, I ,STRTN ODE
ppath,2,FIN IN 0DE
avprin,O,O, 
set,1,1,1,0 
pdef,REALPRES,pres„noavg 
set,1,1,1,1
pdef,IM AG PRES,pres„noavg
paget,tracpo in,poin 
pagetJracdata, tabi 
paget, tradabl, lube
*dim ,RADSPATH,table,N C OU N T,7
*do,IC OU N T,l,N C OU N T
W AVEN U M B =2*PI*FREQU EN C /W ATRSON C
C U RRRADS=TRAC DATA(IC OU N T,2,1)
TEM PAM PL=W ATRDEN S*W ATRSON C *VELOC ITY*W AVEN U M B *(SPHRRADS**2)/C U RRRA 
DS
TEM  PAM PL=TEM PAM PL/( 1 +(W AVEN UM B * SPU RR ADS) * *2)
TEM PAM RC =W AVEN U M B *SPHRRADS*cos(W AVEN U M B *(C U RRRADS-SPHRRADS))
TEM PAM RS=sin(W AVEN UM B *(C U RRRADS-SPHRRADS)) 
TEM PAM IC =cos(W AVEN UM B *(C URRRADS-SPHRRADS)j
TEM PAM IS=-W AVEN U M B *SPHRRADS*sin(W AVEN U M B *(C U RRRADS-SPHRRADS))
RADSPATH(IC OU N T, I )=TRAC DATA(IC OU N T,2,1) 
RADSPATH(IC OU N T,2)=TRAC DATA(IC OUN T,5,1)
RADSPATH(IC OU N T,3)=TEM PAM PL*(TEM PAM RC +TEM PAM RS) 
RADSPATH(IC OUN T,4)=TRAC DATA(IC OU N T,6,1)
RADSPATH(IC OUN T,5>TEM PAM PL*(TEM PAM IC +TEM PAM IS)
RADSPATH(IC OU N T,6)=sqrt(TRAC DATA(IC OUN T,5,l)**2+TRAC DATA(IC OU N T J6,l)**
2)
TEM PI =TEM PAM PL*(TEM PAM RC +TEM PAM RS)
TEM P2 =TEM PAM PL*(TEM PAM IC +TEM PAM IS)
RADSPATII(IC OU N T,7)=sqrt(TEM Pl**2+TEM P2**2)
*cnddo
/gcolum n,! ,AN SYS
/gcolum n,2,Theory
/axlab,x,Radial Distance (tn)
/axlab,y,Real Pressure (Pa)
*vplot,RADSPATI 1(1,1 ),RADSPATH( 1,2),3
/ax lab,y,Im aginary Pressure (Pa)
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N ovem ber 23, 2010
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* vplot,RADSPATH( 1,1 ),RADSPATH( 1.4),5
/axlab,y,M agnitude of Pressure (Pa)
*vplot,RADSPATI 1(1,1 ),RADSPATI 1(1,6),7
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N ovem ber 23, 2010
Page 111


UAP ANSYS Multiphysics RCS Input File Example
/batch „li st
/title, RC S of a Dielectric-coated M etallic Sphere for 300 M U Z (J HF
/com , Problem : A m etallic sphere (radius=5.0m ) coated by dielectric layer
/com , (thickness=1.0m , Er=4)
/com , Incident W ave: -x polirazation with PHI - 0 (degree), THETA = 0 (degree)
/nopr
/prep7
! problem  dim ensions and set-up 
freq=300e6
lam bda=3.e8/freq
epsr=4
wave1-lam bda/sqrt(cpsr)
wave2=lam bda
hl=wavei/25
h2=wave2/25
ra=0.5* lam bda
S=0.01* lam bda
rb^ra+s
a=rb+4*h2
b=a+3*h2
c=b+4*h2
1 — define elem ents and m aterials —
ctJ,HF119,l
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N ovem ber 23, 2010
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et,2,HFH9,1„,l
m p,m urx, 1,1.
m p,perx, 1 ,epsr
m p,m urx,2,l.
m p,perx,2,l.
! — set up the geom etry —
sphere,ra,rb,0,180
sphere,rb,a,0,180
vsel,all
cm ,vequi,volu
block,-b,b,0,b,-b,b
block,-c,c,0,c,-c,c
vsbv,4,3„delete,keep
vsbv,3,vcqui„dclctc,kcep
csys,2
vseI,s,loc,x,0,ra/2
vdel.all
alls
csys,0
vgluc,all
1 — m eshing —
csys,0
sm rtsize,4
! m eshing
esize,hl
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N ovem ber 23, 2010
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type,i
m at,l
vm esh.l
m at,2
esize,h2
vm csh,3
esize,h2
vm csh,6
! — PM L elem ent —
type,2
vm esh,5
alls
num m rg,all
! define equivalent source surface
csys,2
nsel,s,loc,x,0,a
esln,s,l,all
nsel,s,loc,x,a
sf,all,m xwf
alls
! define boundary condition
csys,0
nscl,s,loc,x,c
nsel,a,loc,x,-c
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N ovem ber 23, 2010
Page 114


nsel,a,loc,y,c
nsel,a,loc,z,-c
nsel,a,loc,z,c
d,all,ax,O.
nsel,al!
csys,2
nsel,s,loc,x,ra
d,all,ax,0.
csys,0
allsel,all
! incident plane wave
pl wave,-1,0,0,0,0
fini
/solu
hfscat,scat
eqslv,sparse
aniype.harm ic
harfrq,freq
solve
fini
/post 1
set, 1,1
hfsym ,„pm c
prfar,rcsn, total, 0,0„0,180,36
/yrange,-35,15
pl far,rcsn,total,0,0„0,180,180
fini
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N ovem ber 23, 2010
Page 115


ATTACH MENT II - "TIC TAC’ CH ) CONTOUR PLOTS FOR PRESSURE, 
TEMPERATURE AND MACH NUMBER
1.1 W e *003 
1 000**003 
8 «75 e*002 
7 6 6 0**002 
844$c*002 
5 231**002 
4 016 o002 
2 B0?i-'D 02 
t M 7e*002 
3 727**001
-8 4 * 9 e«-oo
2 05 6 c*
3 E F 1*»
5 root-*
6  0
fl’7a n+
I ip*:
F igure 6 5 . Tic Ta c Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 100 mph with S ubsonic Inlet a nd  
S ubsonic Outlet
2 240**002
2 239 e*002
2 238c*O02
2 23?e*002
2 236 c*002
2 236 **002
2 235 0*002
2 234**002
2 233e*002
2 232r*0
2 232e*
2 231
2 230** 
2 220e*0
2 22&-0
2 226 **00'
2 227c*00?
IKI
F igure 6 6 . Tic Ta c Tempera ture a t 1/6 S ca le, Air Tempera ture 223Ka nd 100 mph with S ubsonic Inlet a nd  
S ubsonic Outlet
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F igure 6 7. Tic Ta c M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 100 mph with S ubsonic Inlet 
a nd S ubsonic Outlet
4 79 7c*003
4 2B0e+003 
3 76 4c*0 0 3 
3.246 e*003 
2 732c*003 
221S e*003
1 183ft0D 3
-3 6 6 2e*0U2
8 825 c*002
I 3B9 c*003
1 &'6 e*-003
2 431e*D 03
-2 M 8e*003 U
3 464c*00 3 "
(Pa ;
F igure 6 8 Tic Ta c Pressure a t 1/6 S ca le. Air Tempera ture 223K a nd  200 mph with S ubsonic Inlet a nd  
S ubsonic Outlet
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[K|
F igure 6 9 . Tic Ta c Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 200 mph with S ubsonic inlet a nd  
S ubsonic Outlet
2 26 Be*002
2 26 5 e*002
2 26 2**002
2 25 8e*002
2 25 5 c*D 02
2 25 2e‘D 02
3.36 4e-001 
3.15 4e-001 
2.9 44n-001 
27346 -001 
25 23c-001 
2 3136 -001
2.l03e-001 
1 89 3e 001 
1.6 83e-001 
1 472*001 
1.282e-00| 
1,05 26 001 
84176 -002 
6 .315 e-002 
4 213tt 00? 
2.111e-002 
9  187C -005
F igure 70. Tic Ta c M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 200 mph with S ubsonic Inlet 
a nd S ubsonic Outlet
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1 135 e»004 
1 0l3e*004 
8 9 13e*003
7 6 9 3e»003 
6  4730+003 
5 25 2e*003
4 032c* C l
2 B1?h 
1
3 7POr»
6 W9e
(Pa !
F igure 71 Tic Ta c Pressure a t 1/6 S ca le. Air Tempera ture 223K a nd 300 mph with S ubsonic Inlet a nd  
S ubsonic Outlet
8 4B*e
2 OW e*W J 
3 2B8e
- 5 08e
2 27Be»002
2 315 e*002
2 308e*002
2 30t>*002
2 29 3e*002
2 285 c*O02
F igure 72 Tic Ta c Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 300 mph with S ubsonic Inlet a nd  
S ubsonic Outlet
M
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£ 477r D OS  
3.246 e 002 I
1 557n0 0 4 "
6  477r D OS
F igure 73. Tic Ta c M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 300 mph with S ubsonic Inlet 
a nd S ubsonic Outlet
5 .171e 001
4 ,848e 001 
4.5 24c-001
4 201e 001
3 878c 001 
15 5 5 c 001 
3 232m00l
2 9 09 c 001
2 5 86 6 -001
2 26 3r 001 
1.9 40c 001 
1 6 17e001
1,29 46 001
9  7080 002
F igure 74 Tic Ta c Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd  400 mph with M ixed Inlet a nd  
S ubsonic Outlet
2010e*004
179 5 e*004
S 3330’0 03
1 5 79 e*QD 4 
1 36 4e*004
1 149 r*0M
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2 3B2e»002
2 36 9 e*002
2 35 6 e+002
2 3436 *002
2 330c*002
2 317e*002
[KI
F igure 75 . Tic Ta c Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 400 mph with M ixed Inlet a nd  
S ubsonic Outlet
6  837^-001
6  409 e001
5 9 82e001
5 5 5 5 e001
5 12Bc-001
4 701s 001
4 274c-001
3 B46 e 001
3 419 e-001
2 9 9 2r 001
2 5 6 5 e-001 E
2 138c 001
1 711k 001
' 283e 001
8 5 6 3c 002
4 29 2e 002 |
2 020c 004 ■
F igure 76 Tic Ta c M a ch Number a t 1/6 S ca le. Air Tempera ture 223K a nd  400 mph with M ixed Inlet a nd  
S ubsonic Outlet
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3 446 **004 
3 082**004 
JT1M 04 
2 35 4**004
1 9 6 9 **004 
1 6 25 **004
I 26 1**00 
8 9 70**00 
5 329 c*003 
1 6 86 **003
1 »Je»OD 3 
5 5 9 5 **003 
9  236 * *003 
1 286 **004 
1 6 5 2**004 
2 3'6 **004 
■ 2 36 0**004
(Pa l
F igure 77 Tic Ta c Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 5 00 mph with M ixed Inlet a nd  
S ubsonic Outlet
2 46 7**002
2 445 **002
2 423**002
2 401**002
2 379 c*002
2 35 7**002
2 335**0 0 2
2 313**002
2 29 1**002
2 26 9 **00?
224Be*002
2 226 **002
2 204**002
216 2**002
216 0**002
2 136 **002 U
2 1'6 **002 ■ 
IKI
F igure 78 Tic Ta c Tempera ture a t 1/6 S ca le. Air Tempera ture 223K a nd 5 00 mph with M ixed Inlet a nd  
S ubsonic Outlet
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B9 79 e 001 
8418e 001 
7 8M C -0O1 
7 29 6 * 001 
6 734c-001 
6 173s 001 
5  6 12O-001 
5  05 1e001 
4 49 00-001 
3 9 29 c 001 
3 36 8C -001 
2 6 07c 001 
2 246 c 001 
• G85 e 001 
1 124c 001 
5 6 3te 002 
2 038n 004
F igure 79 Tic Ta c M a ch Number a t 1/6 S ca le. Air Tempera ture 223K a nd 5 00 mph with M ixed Inlet a nd  
S ubsonic Outlet
1 6 70**006
1 566**0 0 5
1 46 2**005
1 35 7**005
1 25 3**005
1 148**005
1 044**001'
9  39 6 **004
8 35 2**004
7 308c*004
6 26 4* • 004
5 220c‘004
4176 *.004
3 132**004
2 OBBr.OM
1 044**004
0  0 0 0 **0 0 4 —1
F igure 80 Tic Ta c Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd  9 00 mph with S upersonic Inlet a nd  
S upersonic Outlet
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F igure 81 Tic Ta c Tempera ture a t 1/6 S ca le. Air Tempera ture 223K a nd 9 00 mph with S upersonic Inlet 
a nd S upersonic Outlet
1 3036 *000 
1.2226 +000 
1 140*000 
1 05 9 e*000 
».775 b4»1 
8M 2e-001 
8.1*8o-001 
7 334b 001 
6 .5 20e-001 
5 707 p 001 
4.89 36 -001 
4.079 s 001 
3 26 5 6 -001 
2.45 2e001 
• 6 38k 00! 
8 24 le 002 
1.035 C -003
F igure 82. Tic Ta c M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 9 00 mph with S upersonic Inlet 
a nd S upersonic Outlet
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2 0B7t*005  
1 9 5 3e+005
1 819 eH »5
1 6 B6 *t005
1 5 5 2r*005
1 41Be»005
IPS)
F igure 83 Tic Ta c Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 1100 mph with S upersonic Inlet a nd  
S upersonic Outlet
410r»002
336 e*D 02
26 1c*002
1B6 e*002
111Te+W 2
F igure 84 Tic Ta c Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 1100 mph with S upersonic Inlet 
a nd S upersonic Outlet
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1 6 D 6 r*D 00
1 5 M e*000
1 406 e*000
1 305 e*000
1 205 c*000
1 105 e*000
F igure 85 . Tic Ta c M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 1100 mph with S upersonic Inlet 
a nd S upersonic Outlet
1 279 c-003
2 886 fc*005  
Z6 9 3e*005  
2 5 00e»005
2 3D 6 e»005  
2 11 >>005  
1 9 20e»005
F igure 86 Tic Ta c Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 1300 mph with S upersonic Inlet a nd  
S upersonic Outlet
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3?58e*0 0 2
3 6 5 5 e*002
3 5 5 le*002
3 448C +002
3 345 e*002
F igure 87. Tic Ta c Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 1300 mph with S upersonic Inlet 
a nd S upersonic Outlet
1 9 0le*000
1 7B2e*000
1 6 6 4e*000
1 M S efOOO
1 426 c*000
F igure 88. Tic Ta c M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 1300 mph with S upersonic Inlet 
a nd S upersonic Outlet
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ATTACH MENT UI - RIGH T CIRCULAR CYLINDER CFD CONTOUR PLOTS EOR 
PRESSURE, TEMPERATURE AND MACH NUMBER
742let002 
6 .5 6 7e*002
5 714e*002 
4 B6 1e*002 
4 008c*002
3 15 -1^002 
2 33 m*002
1 44Br-0D 2 
5 04$e*00l 
2 5 8&r*001
<r2e»0U2 
1 &5 5 c*002
2B'9 ft002
■3 6 724*002 
A5 2S e*OOJ
5 3^*3U'- 
■6 232c*00?
[Pa :
F igure 89 . C ylind er Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 100 mph with S ubsonic Inlet a nd  
S ubsonic Outlet
2 240e»002 
2 2M e*002
2 238e*0C 2
2 237e*002
2 23?c*002
2 236 e*002
2 235 o
2 2M e»g 
2234e*00
? ?3>*
2 
2231
2 231e>002 
2 230*00
2 22Be*00 
2228^00?
F igure 9 0. C ylind er Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 100 mph with S ubsonic Inlet 
a nd S ubsonic Outlet
[KJ
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1 6 07r 001 
t,5 07*001
1 406 n 001 
1,306 *001
1 205 c-001 
1 105 * 001
F igure 9 1, C ylind er M a ch Number a t 1/6 S ca le. Air Tempera ture 223K a nd 100 mph with S ubsonic Inlet 
a nd S ubsonic Outlet
3 25 4**003 
2 BBS *’■003 
2 5 22**003 
2 15 7**003 
1 79 1**003 
1 425 **003
I 05 9 ^003 
6 9 36 **00- 
3 279 **002 
3 787**00
7 5W e*002
t W ie*W 3
I B6 7-* 00
2 2 32**003 |
?5 ^a **ooi ■
i^:
F igure 9 2. C ylind er Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 200 mph with S ubsonic Inlet a nd  
S ubsonic Outlet
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2 26 8e»002 
2 26 5 e*002 
2 26 2**002 
2 25 9 e*002 
2 25 5 c*002 
2 "5 3**00?
2 25 0**002
2 2476 *002
2 24*1**002 
? 241**002 
2 236 **002 
2 235 **002 
2 232**002
2 22Be*002 
2 226 **002 
2 223**002
2 2200
[K J
F igure 9 3. C ylind er Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 200 mph with S ubsonic Inlet 
a nd S ubsonic Outlet
2 26 8**002
2 26 5 e*002
2 26 2c*002
2 25 0**002
2 25 5 **002
2 25 3**002
2 25 0c*
2 247**0
2 244c*00
2 ?41r*
2 236 6 *
2 232**002
2 22&e*002
2 226 **002
2 223**00i ■
2 220**002 "
[KJ
F igure 9 4. C ylind er M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 200 mph with S ubsonic Inlet 
a nd S ubsonic Outlet
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8 249 **003 
7 419 **003
6 5 89 **003
5 75 9 **003
4 9 29 **003
4 0 98**0 03
3 26 00*003 
2438rt003
I 6 06 **00 
7 777**002
■U 2S *£*W J
8 827**002
I ."3^003 
-2.6 43**003
3 373ftD D 3 
-4 203**003 . 
■ 5 334**003 “
1^1
F igure 9 5 C ylind er Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 300 mph with S ubsonic Inlet a nd  
S ubsonic Outlet
2 316 e*-002 
2 309 **002 
2 302**002 
2 29 5 **002
2 288**002 
2 281**002
2 27 
226 7**0 
22
2 25 3**
(K J
2 246 **0
2 239 **
2 232*
2 225 **00:
2 218**00:
2.211**00:
F igure 9 6 C ylind er Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 300 mph with S ubsonic Inlet 
a nd S ubsonic Outlet
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4 9 5 2^001 
4.6 4 3e 001
4 3.3 > 001
4 024e 001
3 7140-001
3 405 e-001
1.5 481? 001
* 23Be 001
F igure 9 7 C ylind er M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 300 mph with S ubsonic Inlet 
a nd S ubsonic Outlet
1 5 32e*004
1 3M e»004 
t 245 eH »4 
I l02e*-004 
9  5 8ftc+003 
815 6 e»003 
6 724e*003 
5  
3 
n 
9  
4 
•1 
3 
4 
6  
.7
[Pal
F igure 9 8 C ylind er Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd  400 mph with S ubsonic Inlet a nd  
S ubsonic Outlet
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Page I 32


1 5 32c<004 
1 388e*004
1 245 e*0O4
1 102**004 
9  5 W c*003 
815 6 t»003 
6 724c*003
5 2B2r»0W  
3 86 00*003 
2426 c»003 
9  9 5 5 e*002
4 36 5 c*002
1 BB9 c<003 
3 301**003 
4 73>»003 
-6 16 5 **003
7 5 9 7c>003
[PM
F igure 9 9 . C ylind er Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 400 mph with S ubsonic Inlet 
a nd S ubsonic Outlet
6 412c 001 
6 .0H e 001 
5 6 1 On 001 
5  21 Oe 001 
4 009 c-001 
4.408e-001
a rxw-001 
3 6 07 k 001
2105 0 00 
2 404^00
2.0040 00
1 6 03c OOI 
t .202e 001 
8 015 c 002
4 0070 002 
1 000c 015
F igure 100. C ylind er M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 400 mph with S ubsonic Inlet 
a nd S ubsonic Outlet
Sum m ary Report on B AASS IIAP Analysis C apabilities
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2 79 6 e*004
2 5 5 6 e*0M
2 316 e*0M
2 076 e+004
1 836 c+0M
1 5 9 6 m 004
6 35 ?e‘0W  
3 9 5 7e»OO3 
1 5 5 7^003 
fl 436 *->002 
3 243e*00J  
5  6 43^003 
8 C M  3e *003 
1 344r“004
F igure 101. C ylind er Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 5 00 mph with M ixed Inlet a nd  
S ubsonic Outlet
2 46 9 e‘002
245 1e*002
2 414e’002 
2 39 6 o*002 
2 377m 002
2 35 80
(KJ
F igure 102. C ylind er Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 5 00 mph with M ixed Inlet a nd  
S ubsonic Outlet
2 341m 
2 322m
7 3M i-‘ 
2 285 m
2 26 7
2 246 m
Sum m ary Report on B AASS (JAP Analysis C apabilities
N ovem ber 23. 2010
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S  1 05 k 001 
7.5 9 9 6 -0)1 
7 09 2^001 
6 .5 85 eQQ1
9  079 6 -001 
5  5 72e 001
? on 0-00 
4 5 5 9 e 001
4 05 26 -00
3 5 «c 00
3 039 6 -001
2 5 33c 00
3 026 e 001
1 a zo* 001
1 013k 00
1; 05 6 e 002
1 000n-015
F igure 103 C ylind er M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 5 00 mph with M ixed Inlet a nd  
S ubsonic Outlet
7 6 5 6 e*0M  
7.117e*OO4
6 5 79 e*0M  
6 039 e*004 
5 5 00r*004 
4 9 6 1^00-1
42&H JW
F igure 104. C ylind er Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 700 mph with M ixed Inlet a nd  
S upersonic Outlet
3BB3e*00« 
3 34&c-004 
2 B0C e‘D 04 
2 26 7^004 
1 728e*0C !4 
1 1B9 e»004 
6  49 9 e*003 
IH D r^OO’ 
427te*-00: j 
a oW eM W S
! [Ph
Sum m ary Report on B AASS U AP Analysis C apabilities
N ovem ber 23,2010
Page 135


1 140^'005
1 06 9 e*005  
9  9 75 r*004 
9  26 2e*004 
fl 5 5 0*004
7 837c-004
6 4i?cH
5 700e*l
4 M ?eM
4 275 0*1
3 5 6 2c *1
2 35 0e*l
2 I37e*l 
1 4?5 t-‘l 
1 125 e*l
0 D 0D r*l
ipn
F igure 105 . C ylind er Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd  9 00 mph with S upersonic Inlet 
a nd S upersonic Outlet
3.01 Ie *002 
2 9 6 3c-002 
2 9  Ur *002 
286 5 e-002 
2 816 c*002 
2 76 7e*002 
2 71B< *002 
2 6 70c >002 
28210*002 
2 5 7?r*0D ? 
iM  
2 425 e*002 
2 3770*002 
2 328c*002 
227&e*002 
2 P30c*0^
[K I
F igure 106 . C ylind er Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd  9 00 mph with S upersonic Inlet 
a nd S upersonic Outlet
Sum m ary Report on B AASS U AP Analysis C apabilities
N ovem ber 23, 2010
Page 1 36


1 3D >*000
1 222e*000
1 140r*000 
t.05 9 e*000
9  773e-001
B958e 0 0 1
7 3?9 h 001 
6 5 15 0-001 
5 701e 001 
4 886 e-001 
4 072e 001 
3.25 86 -001 
2 +4 3e 001 
1 6 29 k 001 
8 14+0-002 
1 000n-015
F igure 107. C ylind er M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 9 00 mph with S upersonic 
Inlet a nd S upersonic Outlet
1 249 e*005
1 16 3e*005
1 076 rr*005
9  BB8e*004
9  01&c*004
8 IS OeH KH  
7 2830*004 
6 413H 0D + 
5 5 440*004 
4 6 75 r*0p4 
3BO^UC M  
2 9 385 *004 
2 06 9 ^*00+ 
I 200»*0(i4 
3 317e*0(>3 
-5 37-3e*l)03
1 408©*004
[P«l
F igure 108 C ylind er Pressure a t 1/6 S ca le, Air Tempera ture 223K a nd 1100 mph with S upersonic Inlet 
a nd S upersonic Outlet
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N ovem ber 23.20IO
Page 137


3 39 8e*002 
3 32fe*002 
3 25 2c*002 
3l79 e*D 02
3 106 o*002 
3 033e*002 
2 9 8&c*002
2 BB7e«0 12 
2 814o*O 12
2 74ip»OI2 
2 5 6 Be*U(l2 
2 5 9 5 c*002 
2 5 22e*002
2 449 e*0C :
2 376 ^00:
12
12
2 303e*0&2 I
2 2300*0(12 ■
IN
F igure 109 . C ylind er Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 1100 mph with S upersonic 
Inlet a nd S upersonic Outlet
1 5 9 >»0D 0 
1 49 3e*000 
1 39 4«*000
1 2»4e*000
1 19 5 c*000 
1 09 5 #*000 
9 ^0-001
8 9 6 1c 001
7 9 85 e-0()1
6  9 89 c 001
5 9 74e-D 0l 
4 9 78c 001
F igure 110. C ylind er M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 1100 mph with S upersonic 
Inlet a nd S upersonic Outlet
Sum m ary Report on B AASS HAP Analysis C apabilities
N ovem ber 23. 2010
Page 138


1 818e*00S
1 6 9 ^005
1 5 6 0*005
1 431«*00S
1 301c*005
1 172e*D0 5
1 tM 3e*005
9 13fe«004
7 S Uc-OM
6 5 5 6 ^004
5 26 6 c-*004
3 #73eH B4
2 6 8 >*004
1 3W e+O04
9 bi3m oo2
■1 IS ^OtH  .
2 486 ^004 “
[Pa l
F igure 111. C ylind er Pressure a t 1/6  S ca le, Air Tempera ture 223K a nd 1300 mph with S upersonic Inlet 
a nd S upersonic Outlet
3 86 1^*002 
3.7W e+M 2 
3 6 5 7e*002 
3 5 5 5 e*002 
3 45 3c+002 
3 35 0e»D 02 
2 
2 
2 
2 
2 
2
2 6 36 e*002 
2 5 34e*002 
2 432r‘002 
2 330e*0C 2 
2 227e*00 2
F igure 112 C ylind er Tempera ture a t 1/6 S ca le, Air Tempera ture 223K a nd 1300 mph with S upersonic 
Inlet a nd  S upersonic Outlet
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N ovem ber 23, 2010
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1 BB5 f000 
176 7e*000 
1 6 49 r«-000 
1 5 3le*000
1 413c*000 
1 29 6 e*000
F igure 113. C ylind er M a ch Number a t 1/6 S ca le, Air Tempera ture 223K a nd 1300 mph with S upersonic 
Inlet a nd  S upersonic Outlet
Sum m ary Report on B AASS U AP Analysis C apabilities
N ovem ber 23. 2010
Page 140