Have a personal or library account? Click to login
Janus – A New Approach to Air Combat Pilot Training Cover

References

  1. [1] EDIDP (European Defence Industrial Development Programme), EDIDP-ACC-CJTP-2019, Call identifier: Call EDIDP-ACC-2019, Brussels, European Commission;
  2. [2] http://aviationweek.com/defense/multimission-concept-lightweight-advanced-trainers, accessed May 11 2016;
  3. [3] APP Aircraft Performance Program (trade mark) developed and source code owned (not released) by ALR. Commercial product. ALR Zurich, Switzerland;
  4. [4] Hillaker H., YF-16 Design Concept and Philosophy, Paper presented at 23 Israel Annual Conference on Aviation and Astronautics, 11-12 Feb. 1981, Edited by Univ.Michigan, April 1991.
  5. [5] Whitford R., Design for Air Combat, Jane’s Publishing Company Ltd, London 1987.
  6. [6] Asselin M., An Introduction to Aircraft Performance, AIAA Inc., Reston VA, 1997.10.2514/4.861529
  7. [7] Orlik-Rückemann K.J., Aerodynamics of Manoeuvring Aircraft, Canadian Aeronautics and Space Journal, Vol.38, No.3, Sept.1992, pp.106-115.
  8. [8] Herbst W.B., Supermanoeuvrability, Proc. of AFOSR-FJSRL Workshop on Unsteady Separated Flow. Colorado Springs, August 1983.
  9. [9] Robinson B.A., Barnett R.M., Agrawal S., Simple Numerical Criterion for Vortex Breakdown, AIAA Journal, Vol.32, No.1, 1994, pp.116-122.10.2514/3.11958
  10. [10] Orlik-Rückemann K.J., Aerodynamic Coupling between Lateral and Longitudinal Degrees of Freedom, AIAA Journal, Vol.12, No.12, 1977, pp.1792-1799.10.2514/3.60843
  11. [11] Orlik-Rückemann K.J., Dynamic Stability Testing of Aircraft - Needs Versus Capabilities, Prog.Aerospace Sci., Vol.16, No.4, 1975, pp.431-447.10.1016/0376-0421(75)90005-6
  12. [12] Orlik-Rückemann K.J., Aerodynamic Aspects of Aircraft Dynamics at High Angles of Attack, Jour.of Aircraft, Vol.20, No.9, Sept.1983, pp.737-752.10.2514/3.44938
  13. [13] Rom J., High Angle of Attack Aeodynamics, Springer-Verlag, Berlin 1992.10.1007/978-1-4612-2824-0
  14. [14] Gordnier R.E., Computation of Vortex Breakdown on a Rolling Delta Wing, Jour.of Aircraft, Vol.32, No.3, pp.686-688.10.2514/3.46777
  15. [15] Gordnier R., Computation of Delta Wing Roll Maneuvers, Jour.of Aircraft, Vol.32, No.3, May-June 1995, pp.486-492.10.2514/3.46746
  16. [16] Kandil O., Chuang H., Computation of Vortex-Dominated Flow for a Delta Wing Undergoing Pitching Oscillation, Jour. of Aircraft, Vol.28, No.9, Sept.1990, pp.1589-1595.10.2514/3.25257
  17. [17] Kandil O., Chuang H., Influence of Numerical Dissipation on Computational Euler Equations for Vortex-Dominated Flows, AIAA Journal, Vol.25, Nov.1987, pp.1426-1434.10.2514/3.9800
  18. [18] Kandil O., Recent Advances in Multidisciplinary Aeronautical Problems of Fluid/Structures/Dynamics Interaction, Proceedings of Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Z.Goraj, Warsaw 1997, Part I, pp. 15-34.
  19. [19] Menzies M., Kandil O., Natural Rolling Responces of a Delta Wing in Transonic and Subsonic Flows, AIAA Atmospheric Flight Mechanics Conference, AIAA-96-3391, pp.246-254, San Diego 1996.10.2514/6.1996-3391
  20. [20] Kandil O., Kandil H., S.Massey, Simulation of Tail Buffet Using Delta Wing Vertical Tail Configuration, AIAA Atmospheric Flight Mechanics Conference, AIAA-93-3688, pp.566-577, Monterery 1993.10.2514/6.1993-3688
  21. [21] Kandil O., Sheta E., Massey S., Buffet Responses of a Vertical Tail in Vortex Breakdown Flows, AIAA Atmospheric Flight Mechanics Conference, AIAA-95-3464, pp.345-360, Baltimore 1995.10.2514/6.1995-3464
  22. [22] Kandil O., Massey S., Sheta E., Aerostructural Vortical Flow Interactions with Applications to F/A-18 and F-117 Tail Buffet, High-Angle-of-Attack Technology Conference, NASA Langley Research Center, Hampton, VA, Sept.1996, (20 p.).
  23. [23] Hsu C., Liu C., Numerical Study of Vortex-Dominated Flows for Wings at High Incidence and Sideslip, Jour. of Aircraft, Vol.29, No.3, May-June 1992, pp.396-403.10.2514/3.46175
  24. [24] Lopez J., Axisymmetric Vortex Breakdown, J.Fluid Mech., (1990), Vol.221, Part 1. Confined Swirling Flow: pp.533-552, Part 2. Physical Mechanisms: pp.553-576.
  25. [25] Strohmeyer D., Orlowski M., Longo J., Hummel D., Bergmann A., An Analysis of Vortex Breakdown Predicted by the Euler Equations, ICAS Proceedings, 96-1.6.3., pp.1189-1200, Sorento 1996.
  26. [26] Boffadossi M., Calculation of Vortex Breakdown over „delta” Wing by a Vortex-Lattice Method, ICAS Proc. of 20th Congress, Sorrento, Sept.1996, pp.1201-1210.
  27. [27] Robinson B.A., Barnett R.M., Agrawal S., Simple Numerical Criterion for Vortex Breakdown, AIAA Journal, Vol.32, No.1, 1994, pp.116-122.10.2514/3.11958
  28. [28] Gursul I., Criteria for Location of Vortex Breakdown over Delta Wings, Aeronautical Journal, May 1995, pp.194-196.10.2514/6.1994-536
  29. [29] Luckring J., Aerodynamics of Strake-Wing Interaction, Journ. of Aircraft, Vol.16, No.11, Nov.1979, pp.756-762.10.2514/3.58600
  30. [30] Polhamus E.C., A Concept of the Vortex Lift of Sharp-Edge Delta Wing based on a Leading-Edge-Suction Analogy, NASA TN D-3767, 1966.
  31. [31] Polhamus E.C., Predictions of Vortex-Lift Characterisctics by a Leading-Edge Suction Analogy, Journ.of Aircraft, Vol.8, No.4, April 1971, pp.193-199.10.2514/3.44254
  32. [32] Vizel E., Gontchar A., Investigations of Aerodynamic Characteristics of Part-Scale Aircraft Model of Moderate Wing Sweep Angle and the Structure of Vortices versus the LEX’s Form-in Plane and its Parameters, (In Russian), Journal - Technika Vojennogo Flota (TBФ), No.1-2, 1994, pp.52-58.
  33. [33] Tu E.L., Vortex-Wing Interaction of a Close-Coupled Canard Configuration, Jour. of Aircraft, Vol.31, No.2, 1994, pp.314-321.10.2514/3.46489
  34. [34] Gordnier R., Visbal M., Unsteady Vortex Structure over a „delta” Wing, Jour. of Aircraft, Vol.31, No.1, Jan.-Feb. 1994, pp.243-248.10.2514/3.46480
  35. [35] Wood R., Miller D., Assessment of Preliminary Prediction Techniques for Wing Leading-Edge Vortex Flows at Supersonic Speeds, Jour.of Aircraft, Vol.22, No.6, June 1985, pp.473-485.10.2514/3.45151
  36. [36] Delery J., Aspects of Vortex Breakdown, Prog. Aerospace Sci., Vol.30, pp.1-59, 1994.10.1016/0376-0421(94)90002-7
  37. [37] Ekaterinaris J.A., Schiff L.B., Navier-Stokes Solutions for an Oscillating Double-delta Wing, J. Of Aircraft, 32, 2, 1995, pp.228-234.10.2514/3.46708
  38. [38] Cornelius K.C., Analysis of Vortex Bursting Utilizing Three-Dimensional Laser Measurements, Journ. of Aircraft, Vol.32, No.2, March-April 1995, pp.297-306.10.2514/3.46716
  39. [39] Hoeijmakers H., Computational Vortex Flow Aerodynamics, AGARD CP-342, 1983, No. 18, pp.18.1-18.35.
  40. [40] Hitzel S.M., Schmidt W., Slender Wings with Leading-Edge Vortex Separation - a Challenge for Panel-Methods and Euler-Codes, AIAA Paper 83-0262, 1983.10.2514/6.1983-562
  41. [41] Ericson L., Challenges in High-Alpha Vehicle Dynamics, Prog. Aerospace Sci., Vol.31, pp.291-334, 1995.10.1016/0376-0421(95)00002-G
  42. [42] Ericson L., Pitch Rate Effects on „delta” Wing Vortex Breakdown, Journal of Aircraft, Vol.33, No.3, May-June 1996, pp.639-642.10.2514/3.46998
  43. [43] Ericson L., Delta Wing Vortex Breakdown Dynamics, AIAA Paper 95-0367, Jan.1995.10.2514/6.1995-367
  44. [44] Khrabrov A., Kolinko K., Experimental Investigations of the High Aspect Ratio Wing Unsteady Aerodynamics at Stall Regimes and its Mathematical Modeling, Proceedings of Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Goraj Z., Warsaw 1997, Part I, pp. 195-200.
  45. [45] Khrabrov A., Miatov O., Experimental and Theoretical Investigations of Delta Wing High Angles of Attack Unsteady Aerodynamics, Proceedings of Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Goraj Z., Warsaw 1997, Part I, pp. 201-206.
  46. [46] Greenwell D., Wood N., Some Observations on the Dynamic Response to Wing Motion of the Vortex Burst Phenomenon, Aeronautical Journal, Feb.1994, pp.49-59.10.1017/S000192400005020X
  47. [47] Mabey D., Unstedy Vortex Flow Phenomena on „delta” Wings at High Angles of Incidence, ICAS Proceedings, 96-1.6.1., pp.1167-1176, Sorento 1996.
  48. [48] Alcorn C., Croom M., Francis M., Ross H., The X-31 Aircraft: Advances in Aircraft Agility and Performance, Prog. Aerospace Sci., Vol.32, pp.377-413, 1996.10.1016/0376-0421(95)00006-2
  49. [49] Dzelnin Yu., Aircraft Stability and Maneuverability During Dynamic Departure at High Angles of Attack (In Russian), Journal - Technika Vojennogo Flota (TBФ), No 1-2, 1994, pp.59-66.
  50. [50] J.Rom, High Angle of Attack Aerodynamics - the State of Art and Future Challenges, Proceedings of Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Goraj Z., Warsaw 1997, Part I, pp.41-54.
  51. [51] Goraj Z., New Directions of Research in Aeronautical Engineering - Breaking the Barriers, Journal of Theoretical and Applied Mechanics, 4, 35, 1997, pp.781-812.
  52. [52] Pamadi B.N., Performance, Stability, Dynamics, and Control of Airplanes, AIAA Education Series, 1998.
  53. [53] Payne F.M., Nelson R.C., An Experimental Study of Vortex Breakdown on a Delta Wing, NASA CP-2416, 1992.
  54. [54] Skow A.M., Titriga A.Jr., Moore W.A., Forebody-Wing Vortex Interactions and their Influence on Departure and Spin Resistance, CP-247, AGARD, paper 6, 1979.
  55. [55] NASA Report TP 2011, Exploratory Study of the Effects of Wing-Leading Edge Modifications on the Stall/Spin Behaviour of a Light General Aviation Airplane, Washington DC, 1982.
  56. [56] DiCarlo D.J., Glover K.E., Stewart E.C., Stough H.P., Discontinuous Wing Leading Edge to Enhance Spin Resistance, Journal of Aircraft, Vol.22, 4, 1985, pp.283-288.10.2514/3.45121
  57. [57] Ghmman A.H., Goraj Z., Review On The Influence Of High Angle Of Attack Aerodynamics On Aircraft Dynamic Stability, Jour.Theor. Appl.Mech., 3, 33, 1995, pp.667-686.
  58. [58] Ross A.J., Investigation of Nonlinear Motion Experienced on a Slender-Wing Research Aircraft, Journal of Aircraft, Vol.9, 1972, pp.625-631.10.2514/3.59050
  59. [59] Ericson L.E., Wing Rock Generated by Forebody Vortices, AIAA Paper 87-0268, 1987.10.2514/6.1987-268
  60. [60] Murri D., Shah G., DiCarlo D., Actuated Forebody Strake Controls for the F 18 High Alpha Research Vehicle, Journal of Aircraft, Vol.32, 3, May-June 1995, pp.555-562.10.2514/3.46755
  61. [61] Ng T.T., Suarez C.J., Kramer B.R., Ong L.Y., Ayers B., Malcolm G.N., Forebody Vortex Control for Wing Rock Supression, Journal of Aircraft, Vol.31, 2, 1994, pp.298-305.10.2514/3.46487
  62. [62] Murri D.G., Nguyen L.T., Grafton S.B., Wind-Tunnel Free-Flight Investigation of a Model of a Forward-Swept-Wing Fighter Configuration, NASA TP 2230, Feb.1984.
  63. [63] Hsu C.H., Lan C.E. Theory of Wing Rock, J.of Aircraft 1985, Vol.22, No.10, pp.920-924.10.2514/3.45225
  64. [64] Weissman R., Status of Design Criteria for Predicting Departure Characteristics and Spin Susceptibility, Journal of Aircraft, Vol.12, 12, 1975, pp.989-993.10.2514/3.59904
  65. [65] Hillaker H., YF-16 Design Concept and Philosophy, Paper presented at 23 Israel Annual Conference on Aviation and Astronautics, 11-12 Feb. 1981, Edited by Univ.Michigan, April 1991.
  66. [66] Bitten R., Operational Benefits of Thrust Vectoring (TVC), NASA CP-3149, Part 2, Vol.I, 1990, pp.587-601.
  67. [67] Grafton S.B., Libbey Ch.E., Dynamic Stability Derivatives of a Twin-Jet Fighter model for Angles of Attack from -10o to 110o, NASA TN D-6091, Washington Jan.1971.
  68. [68] Busemann A., Aerodynamic Forces at Supersonic Speeds, Luftfahrtforschung, Vol.12, No 6, Oct.3, 1935.
  69. [69] Wilson H.A., Lovell J.C., Full Scale Investigation of the Maximum Lift Flow Characteristics on an Airplane Having Approximately Triangular Planform, NACA RM L6K20, Nov.1946.
  70. [70] Peckham D.H., Atkinson S.A., Preliminary Results of Low Speed Wind Tunnel Test on a Gothic Wing of Aspect Ratio 1.0, Aeronautical Research Council, CP 508, April 1957.
  71. [71] Werle H., Sur l’eclatement des tourbillions d’apex d’une aile delta aux faibles vitesses, La Recherche Aeronautique, No.74, Jan/Feb 1960.
  72. [72] Lambourne N.C., Bryer D.W., The Bursting of Leading Edge Vortices – Some Observationa and Discussion of the Phenomenon, Report and Memoranda No.3282, Aeronautical Research Council, April 1961.
  73. [73] Squire H.B., Analysis of the Vortex Breakdown Phenomenon, Part I, Imperial College of Science and Technology, Aeronautics Department, Report No.102, August 1960.
  74. [74] Taylor S.L. et.al., Experimental and Computational Study of the Subsonic Flow About a 75° Swept Delta Wing, AIAA Paper 87-2425.
  75. [75] Gordnier R.E., Visbal M.R., Numerical Simulation of the Unsteady Vortex Structure Over a Delta Wing, AIAA Paper 91-1811.
  76. [76] Webster W.P., Shang J.S., Numerical Simulation of Vortex Breakdown Over a Delta Wing, AIAA Paper 91-1814.
  77. [77] Kandil O.A., Kandil H.A., Liu C.H., Shock Vortex Interaction Over a 65° Delta Wing in Transonic Flow, AIAA Paper 93-2973.
  78. [78] Aerodynamic Staff of the National Physical Laboratory, Technical Report by the Accident Investigation Subcommittee on the Accident to the Aeroplane G AAZK at Meopham, Kent (England), on 21 July 1930, Aeronautical Research Council, Report and Memoranda No.1360, 1931.
  79. [79] White J.A., Hood M.J., Wing Fuselage Interference, Tail Buffeting and Air Flow About the Tail of a Low Wing Monoplane, NACA Technical Report No.482, 1934.
  80. [80] Abdrashitov G., Tail Buffeting, TsAGI, Moscow, Report No.395, 1935, NACA TM 1041, 1943.
  81. [81] Triplett W.E., Pressure Measurement on Twin Vertical Tails in Buffeting Flow, Journal of Aircraft, Vol.20, No.1, 1983, pp.920-925.10.2514/3.48193
  82. [82] Ericson G.E. et.al., Experimental Investigation of the F/A 18 Vortex Flows at Subsonic Through Transonic Speeds, AIAA Paper 89 2222.
  83. [83] Cole S.R., Moss S.W., Doggett Jr. R.V., Some Buffet Response Characteristics of a Twin Vertical Tail Configuration, NASA TM 102749, Oct.1990.
  84. [84] Lee B.H.K. et.al., Wind Tunnel Investigation of Tail Buffet on the F-18 Aircraft, Paper 1, AGARD Conference Proceedings No.483, 1990.10.2514/6.1990-1432
  85. [85] Washburn A.E., Jenkins L.N., Ferman M.A., Experimental Investigation of Vortex Fin Interaction, AIAA Paper 93 0050.
  86. [86] Rizk Y.M., Guruswamy G.P., Gee K., Numerical Investigation of Buffet on F 18 Aircraft, AIAA Paper 92-2673.
  87. [87] Kandil O.A., Kandil H.A., Massey S.J., Simulation of Tail Buffet Using Delta Wing Vertical Tail Configuration, AIAA 93-3688 CP, pp.566-577.
  88. [88] Kandil O.A., Flanagan M.W., Vertical Tail Buffet in Vortex Breakdown Flows, 5th International Symposium on Computational Fluid Dynamics, Sendai, Japan, August 31 Sept.3, 1993.
  89. [89] Kandil O.A., Massey S.J., Kandil H.A., Computations of Vortex Breakdown Induced Tail Buffet Undergoing Bending and Torsional Vibrations, AIAA Paper 94-1428.
  90. [90] Hirsch C.: Numerical Computation of Internal and External Flows, Vol 1-2, 1988.
  91. [91] Beam R.M., Warming R.F., An Implicit factored Scheme for the Compressible Navier Stokes Equations, AIAA Journal, Vol.16, No.4, 1978, pp.393-402.10.2514/3.60901
  92. [92] Steger J.L., Warming R.F., Flux Vector Splitting of the Inviscid Gasodynamic Equations with Application to Finite Difference Methods, NASA TM 78605, July 1979 (also Journal Of Comp.Physics, Vol.40, No.2, April 1981, pp.263-293).10.1016/0021-9991(81)90210-2
  93. [93] Van Leer B., Flux Vector Splitting for the Euler Equations, ICASE Report 82-30, Sept.1982 (also Lecture Notes in Physics, Vol.170, 1982, pp.507-512).10.1007/3-540-11948-5_66
  94. [94] Thomas J.L., Van Leer B., Walters R.W., Implicit Flux Schemes for the Euler Equations, AIAA Paper 85-1680.
  95. [95] Massey S.J., A Direct Numerical Simulation of Vortex Braekdown Induced Tail Buffet, M.Sc. Degree Thesis, Old Dominion University, May 1994, (unpublished).
  96. [96] Kandill O.A., Recent Advances in Multidisciplinary Aeronautical Problems of Fluids/Structures/Dynamics Interaction, Proceedings of Second International Seminar RRDPAE_1996, Edited by Z.Goraj, Warsaw 1996, pp.15-34.
  97. [97] Küchemann D., The aerodynamic design of aircraft. Pergamon Press, Oxford 1978.
  98. [98] AGARD Conference Proceedings CP 319, Combat Aircraft Manoeuvrability, Dec.1981.
  99. [99] Mabey D.G., Some aspecs of aircraft dynamic loads due to flow separation. Progress in Aerospace Science, No. 2, 1989.10.1016/0376-0421(89)90006-7
  100. [100] Mabey D.G., An hypothesis for the prediction of flight penetration of ming buffeting from dynamic tests of a wind tunnel model. ARC CP 1171, 1971.
  101. [101] Kania W., Gnarowski W., Jóźwiak R., Stalewski W., Wysocki Z., Zwierchanowska B., Żółtak J., Aerodynamic Design and Wind Tunnel Tests of Advanced Attack Aircraft Cobra 2000, Proc.of the Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, Part I, Edited by Z.Goraj, Warsaw 1997, pp.169-174.
  102. [102] Romanowski R., Low Speed Tests of the Dorsal Intake Pressure Recovery for Cobra 2000 Aircraft, Proc.of the Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, Part II, Edited by Z.Goraj, Warsaw 1997, pp.63 -68.
  103. [103] Holligsworth E.H., Lohen M., Determination of F 4 Aircraft Transonic Buffet Characteristics, Jour. of Aircraft, Vol.8. No.10, October, 1971.10.2514/3.59167
  104. [104] Damstrom E.K., Mayes J.F., Transonic Flight and Wind Tunnel Buffet Onset Investigation of the F 8D Aircraft, Jour. of Aircraft, Vol.8. No.4, April, 1971.10.2514/3.44266
  105. [105] Herbst W., Dynamics of Air Combat, J.Aircraft, Vol.20, No.7, July 1983, pp.594-598.10.2514/3.44916
  106. [106] Samoilovitch O., Aerodynamic Configurations of Contemporary and Prospective Fighters, Proc.of Second Seminar on “Recent Research and Design Progress on Aeronautical Engineering and its Influence on Education”, edited by Z.Goraj, Warsaw, Nov. 1996, part II, pp.233-246.
  107. [107] Rom J., High Angle of Attack Aerodynamics the State of Art and Future Challenges, Proceedings of Second Seminar on “Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Goraj Z., Warsaw 1997, Part I, pp.41-54.
  108. [108] Alcorn C., Croom M., Francis M., Ross H., The X 31 Aircraft: Advances in Aircraft Agility and Performance, Progr. Aerosp. Sc., Vol.32, pp.377-413, 1996.10.1016/0376-0421(95)00006-2
  109. [109] Whitford R., Fundamentals of Fighter Design, Cycle 6 papers in Air International, 1996-97.
  110. [110] Delery J.M., Aspects of Vortex Breakdown, Progr. Aerosp. Sc., 30, 1994, pp.1-59.10.1016/0376-0421(94)90002-7
  111. [111] Lopez J., Axisymmetric Vortex Breakdown, J.Fluid Mech., (1990), Vol.221, Part 1. Confined Swirling Flow: pp.533-552, Part 2. Physical Mechanisms: pp.553-576.10.1017/S0022112090003664
  112. [112] Boffadossi M., Calculation of Vortex Breakdown over Delta Wing by a Vortex Lattice Method, ICAS Proc. of 20th Congress, Sorrento, Sept.1996, pp.1201-1210.
  113. [113] Robinson B.A., Barnett R.M., Agrawal S., Simple Numerical Criterion for Vortex Breakdown, AIAA Journal, Vol.32, No.1, 1994, pp.116-122.10.2514/3.11958
  114. [114] Gursul I., Criteria for Location of Vortex Breakdown over Delta Wings, Aeronautical Journal, May 1995, pp.194-196.10.2514/6.1994-536
  115. [115] Luckring J., Aerodynamics of Strake Wing Interaction, Journ.of Aircraft, Vol.16, No.11, Nov.1979, pp.756-762.10.2514/3.58600
  116. [116] Vizel E., Gontchar A., Investigations of Aerodynamic Characteristics of Part Scale Aircraft Model of Moderate Wing Sweep Angle and the Structure of Vortices versus the LEX’s Form in Plane and its Parameters, (In Russian), Journ. Technika Vojennogo Flota, No 1-2, 1994, pp.52-58.
  117. [117] Yu Dzelnin, Aircraft Stability and Maneuverability During Dynamic Departure at High Angles of Attack (In Russian), Journal - Technika Vojennogo Flota (TBФ), No 1 2, 1994, pp.59-66.
  118. [118] Ericsson L., Challenges in High Alpha Vehicle Dynamics, Progr. Aerosp. Sc., Vol.31, pp.291-334, 1995.10.1016/0376-0421(95)00002-G
  119. [119] Ericsson L., King H., Rapid Prediction of High Alpha Unsteady Aerodynamics of Slender Wing Aircraft, Journ.of Aircraft, Vol.29, No.1, Jan. Feb.1992, pp.85-92.10.2514/3.46129
  120. [120] Ericsson L., Pitch Rate Effects on Delta Wing Vortex Breakdown, Vol.33, No.3, May-June 1996, pp.639-642.10.2514/3.46998
  121. [121] Ericsson L., Delta Wing Vortex Breakdown Dynamics, AIAA Paper 95-0367, Jan.1995.10.2514/6.1995-367
  122. [122] Khrabrov A., Kolinko K., Experimental Investigations of the High Aspect Ratio Wing Unsteady Aerodynamics at Stall Regimes and its Mathematical Modeling, Proceedings of Second Seminar on “Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Z.Goraj, Warsaw 1997, Part I, pp. 195-200.
  123. [123] Khrabrov A., Miatov O., Experimental and Theoretical Investigations of Delta Wing High Angles of Attack Unsteady Aerodynamics, Proceedings of Second Seminar on “Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Z.Goraj, Warsaw 1997, Part I, pp. 201-206.
  124. [124] Norris G., Breaking the Stall Barrier, Flight International, 11-17 Nov.1992, pp.34-37.
  125. [125] Ghmmam A.A., Goraj Z., A Review of the Influence of High Angle of Attack Aerodynamics on Aircraft Dynamic Stability, Jour.Ther.Appl.Mech., 3, 33, 1995, pp.667-686.
  126. [126] Well K.H., Faber B., Berger E., Maneuver Optimization of Aircraft Utilizing High Angles of Attack, ICAS Proceedings, 80-6.4., pp.257-264, 1980.
  127. [127] Manor D., Wentz Jr. W., Flow over Double-Delta Wing and Wing Body at High Alpha, Jour.of Aircraft, Vol.22, No.1, Jan.1985, pp.78-82.10.2514/3.45083
  128. [128] Tu E.L., Vortex Wing Interaction of a Close Coupled Canard Configuration, Jour.of Aircraft, Vol.31, No.2, March-April 1994, pp.314-321.10.2514/3.46489
  129. [129] Beyers M.E., Interpretation of Experimental High-Alfa Aerodynamics - Implications for Flight Prediction, Jour. of Aircraft, Vol.32, No.2, March April 1995, pp.247-261.10.2514/3.46710
  130. [130] Beyers M., Investigation of High Manoeuvrability Flight Vehicle Dynamics, ICAS Proceedings, 80 7.2., pp.278-292, 1980.
  131. [131] John H., Kraus W., High Angle of Attack Characteristics of Different Fighter Configurations, AGARD-CP-247, Paper 2(15), 1979.
  132. [132] Rom J., High Angle of Attack Aerodynamics; Subsonic, Transonic, and Supersonic Flows, Springer Verlag, New York 1992. Week & Space Technology, Aug.8, 1994, p.54.10.1007/978-1-4612-2824-0
  133. [133] Chambers J.R.,Overview of Stall/Spin Technology, AIAA Paper 80-1580, Danvers Aug.1980.10.2514/6.1980-1580
  134. [134] Goraj Z., Aerodynamics For High AOA And Introduction Of Polish Aviation Study, Proceedings of The 35th Aircraft Symposium, Tokyo 1997, pp.177-180.
  135. [135] Tu E.L., Effect of Canard Deflection on Close-Coupled Canard-Wing-Body Aerodynamics, Jour.of Aircraft, Vol.31, No.1, Jan.-Feb. 1994, pp.138-145.10.2514/3.46466
  136. [136] Hummel D., Oelker H., Effects of Canard Position on Aerodynamic Characteristics of a Close Coupled Canard Configuration at Low Speed, Z.Flugwiss. Weltraumforsch.15 (1991), pp.74-88.
  137. [137] Kendall E.R., Learjet G., The Minimum Induced Drag, Longitudinal Trim and Static Longitudinal Stability of Two Surface and Three Surface Airplanes, AIAA-84-2164.
  138. [138] Ericsson L., Cobra Maneuver Unsteady Aerodynamic Considerations, Jour.of Aircraft, Vol.32., No.1, pp.214-216.10.2514/3.46706
  139. [139] Ransom S., Configuration Development of a Research Aircraft with Post Stall Manoeuvrability, J.Aircraft, Vol.20, No.7, July 1983, pp.599-605.10.2514/3.44917
  140. [140] Gütter R., Friehmelt H., Haiplik R., Tactical Utility of the X 31A Using Post Stall Technologies, ICAS Proceedings, 96-3.7.5., pp.1574-1583, Sorento 1996.
  141. [141] Grafton S.B., Libbey Ch.E., Dynamic Stability Derivatives of a Twin Jet Fighter model for Angles of Attack from 10° to 110°, NASA TN D 6091, Washington Jan.1971.
  142. [142] Grafton S.B., Anglin E.L., Dynamic Stability Derivatives at Angle of Attack from -5° to 90° for the Variable Sweep Fighter Configuration with Twin Vertical Tails, NASA TN D-6909, Washington Oct.1972.
  143. [143] Goraj Z., High Angles Of Attack Flight Dynamics Of Contemporary And Prospective Fighters As A Function Of Their Configuration And Aerodynamics. Proceedings of 21th Congress of the International Council of the Aeronautical Sciences, ICAS-98-1.7.5, 13-18 September 1998, Melbourne.
  144. [144] Fomin A., Su 27 Flanker Story. Air Fleet Russian Air Force, Aircraft & Space Review, Publisher: RA Intervestnik 2000.
  145. [145] Goraj Z., Aerodynamics & Dynamics of Manoeuvrable Aircraft with Elements of Computing, Scientific Series of Institute of Aviation, Vol.13, 473 pages, Warsaw 2001 (in Polish).
Language: English
Page range: 7 - 22
Published on: Dec 26, 2019
In partnership with: Paradigm Publishing Services
Publication frequency: 4 issues per year

© 2019 Georges Bridel, Zdobyslaw Goraj, Lukasz Kiszkowiak, Jean-Georges Brévot, Jean-Pierre Devaux, Cezary Szczepanski, published by ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.