Implications of scale effect for the prediction of high angle of attack aerodynamics

Progress in Aerospace Sciences

Volumn 41, Issue 3-4, 2005, Pages 301-322

  Munro, C D ^a   Krus, P ^a   Jouannet, C ^a  

^a LINKÖPING UNIVERSITY   (Sweden)

Author keywords

[No Author keywords available]

Indexed keywords

AIRCRAFT; DATA REDUCTION; DECISION MAKING; MACHINE DESIGN; REYNOLDS NUMBER; WINGS;

AERODYNAMICS TESTING; AIRCRAFT DESIGNS; MACH NUMBER; WATER TUNNELS;

AERODYNAMICS;

EID: 22844445824     PISSN: 03760421     EISSN: None     Source Type: Journal    
DOI: 10.1016/j.paerosci.2005.05.001     Document Type: Review

References (89)

1. Erickson GE, Hall RM, Banks DW, Frate JHD, Schreiner JA, Hanley RJ, Pulley CT. Experimental investigation of the F/A-18 vortex flows at subsonic through transonic speeds. AIAA Paper 89-2222; 1989.
2. Werlé H. Survey of the experimental capabilities of the ONERA hydrodynamic tunnel, which offers Flow visualization. ONERA NT-48; 1958.
3. Malcolm GN, Nelson RC. Comparison of water and wind tunnel flow visualization results on a generic fighter configuration at high angles of attack. AIAA Paper 87-2423; 1987.
4. Kegelman JT, Roos FW. The flowfields of bursting vortices over moderately swept delta wings. AIAA 90-0599; 1990.
5. Lambourne NC, Bryer DW. The bursting of leading-edge vortices - some obersvations and discussion of the phenomenon. R. & M. No. 3282, Aeronautical Research Council; 1962.
6. R.C. Nelson, and A. Pelletier The unsteady aerodynamics of slender wings and aircraft undergoing large amplitude maneuvers Prog Aerospace Sci 39 2003 3
7. Schaeffler NW. All the king's horses: the delta wing leading edge vortex system undergoing vortex breakdown. Ph.D. thesis, Virginia Tech; 1998.
8. M. Gad-el Hak, and R.F. Blackwelder The discrete vortices from a delta wing AIAA J 23 1985 6
9. Payne FM. The structure of leading edge vortex flows including vortex breakdown. Ph.D. thesis, University of Notre Dame; 1987.
10. Washburn AE, Visser KD. Evolution of vortical structures in the shear layer of delta wings. AIAA paper 94-2317; 1994.
11. Jarrah M-AM. Low-speed wind-tunnel investigation of flow about delta wings, oscillating in pitch to very high angles of attack. AIAA paper 89-0295; 1989.
12. Roos FW, Kegelman JT. An experimental investigation of sweep-angle influence on delta-wing flows. AIAA paper 90-0383; 1990.
13. Skow AM, Erickson GE. Modern fighter aircraft design for high-angle-of-attack maneuvering. In: High Angle-of-Attack Aerodynamics, AGARD-LS-121; 1982.
14. Sarpkaya T. Vortex breakdown and turbulence. AIAA paper 95-0433; 1995.
15. M. Escudier Vortex breakdown: observations and explanations Prog Aerospace Sci 25 1988
16. J.H. Faler, and S. Leibovich An experimental map for the internal structure of a vortex breakdown J Fluid Mech 86 1978 0
17. Greenwall D. Pitfalls in the interpretation of delta wing flow visualisation. In: Advanced flow management/park A: vortex flow and high angle of attack, RTO MP-069; 2001.
18. Shih C, Ding Z. Unsteady structure of leading-edge vortex flow over a delta wing. AIAA paper 96-0664; 1996.
19. Munro C. Water tunnel validation and experiments at high angles of attack for aircraft conceptual design. Ph.D. thesis, Linköping University; 2003.
20. Görtz S. Steady and unsteady cfd simulations of vortex breakdown over swept delta wings. Licentiate thesis, Royal Institute of Technology, Sweden; September 2002.
21. Ol MV. An experimental investigation of leading edge vortices and passage to stall of nonslender delta wings. In: Advanced flow management/part A: vortex flow and high angle of attack, RTO MP-069; 2001.
22. S.K. Hebbar, M.F. Platzer, and W. Chang Control of high-incidence vortical flow on double-delta wings undergoing sideslip J Aircraft 34 1997 4
23. Myose RY, Lee B-K, Hayashibara S, Millar LS. An experimental study on the breakdown of leading-edge vortices on diamond, cropped, delta and double delta wings during dynamic pitching. AIAA paper 97-1930; 1997.
24. M. Menke, H. Yang, and I. Gursul Experiments on the unsteady nature of vortex breakdown over delta wings Exp Fluids 27 1999
25. Menke M, Gursul I. Self-excited oscillations of vortex breakdown location over delta wings. AIAA paper 97-0744; 1997.
26. Menke M, Yang H, Gursul I. Further experiments on fluctuations of vortex breakdown location. AIAA paper 96-0205; 1996.
27. Mitchell AM, Barberis D, Délery J. oscillation of vortex breakdown location and its control by tangential blowing. AIAA paper 98-2914; 1998.
28. Hanley RJ, Dunaway DA, Lawson KP. Operational lessons learned from the F/A-18E/F total flight control systems integration process. In: Active control technology for enhanced performance operational capabilities of military aircraft, land vehicles and sea vehicles, RTO MP-051; 2000.
29. Cobleigh BR. High-angle-of-attack yawing moment asymmetry of the X-31 aircraft from flight test. AIAA paper 94-1803; 1994.
30. Keener ER. Flow-separation patterns on symmetric forebodies. NASA TM-86016; 1986.
31. Moskovitz CA, Hall RM, DeJarnette FR. Effects of nose bluntness, roughness and surface pertubations on the asymmetric flow past slender bodies at large angles of attack. AIAA paper 89-2236; 1989.
32. Degani D. Numerical investigation of the origin of vortex asymmetry. AIAA paper 90-0593; 1990.
33. Keener ER, Chapman GT. Onset of aerodynamic side forces at zero sideslip on symmetric forebodies at high angles of attack. AIAA paper 74-770; 1974.
34. Suárez CJ, Malcolm GN. Water tunnel force and moment measurements on an F/A-18. AIAA paper 94-1802; 1994.
35. Suárez CJ, Malcolm GN. Dynamic water tunnel tests for flow visualization and force/moment measurements on maneuvering aircraft. AIAA paper 95-1843; 1995.
36. Cunningham Jr. AM, Bushlow T, Mercer JR, Wilson TA, Schwoerke SN. Small scale model tests in small wind and water tunnels at high incidence and pitch rates. Test program and discussion of results, vol. 1. NASA AD-A20864; 1989.
37. Beyers M. From water tunnel to post-stall flight simulation - the F/A-18 investigation. AIAA paper 2002-0699; 2002.
38. Cai HJ, Beyers ME. Overview of rotary flow visualization results on the F/A-18 aircraft. In: 23rd international congress of aeronautical sciences. ICAS-2002-3.10.4; 2002.
39. A.B. Haines Scale effects on aircraft and weapon aerodynamics AGARDograph 323 1994
40. Holze C, Oelze HW, Rath HJ. Pressurized temperature-variable water tunnel for high Reynolds number research. AIAA paper 2002-0701; 2002.
41. J.B. Barlow, W.H. Rae Jr., and A. Pope Low-speed wind tunnel testing 3rd ed 1999 New York Wiley
42. Banks DW, Fisher DF, Hall RM, Erickson GE, Murri DG, Grafton SB, Sewall WG. The F/A-18 high-angle-of-attack ground-to-flight correlation: lessons learned. NASA TM-4783; 1997.
43. Beyers ME and Ericsson L. Why is LEX vortex breakdown on the F/A-18 configuration insensitive to Reynolds number? AIAA 2001-0690; 2001.
44. A.M. Kuethe, and Y. Chow C- Fundamentals of aerodynamics: bases of aerodynamic design 4th ed 1986 New York Wiley
45. D. Arnal, and G. Casalis Laminar-turbulent transition prediction in three-dimensional flows Prog Aerospace Sci 36 2000 2
46. Mabey DG. A review of scale effects in unsteady aerodynamics. In: Proceedings of 17th international congress of aeronautical sciences. ICAS-90-3.4.1; 1990.
47. Reichenbach SH, McMasters JH. A semiempirical interpolation technique for predicting full-scale flight characteristics. AIAA Paper 87-0427; 1987.
48. Erickson GE. Vortex flow correlation, AFWAL-TR-80-3143; 1981.
49. Johnson FT, Lu P, Brune GW, Weber JA, Rubbert PE. An improved method for the prediction of completely three-dimensional aerodynamic load distributions of configurations with leading edge vortex separation. AIAA 76-417; 1976.
50. Earnshaw PB, Lawford JA. Low-speed wind-tunnel experiments on a series of sharp-edged delta wings. Report no. 3424, Aeronautical Research Council; 1966.
51. Taylor GS, Schnorbus T, Gursul I. An investigation of vortex flows over low sweep delta wings. AIAA Paper 2003-4021; 2003.
52. Huang XZ, Hanff ES. Motion effects on leading-edge vortex behaviour over delta wings and generalized modelling. In: Advanced flow management/part A: vortex flow and high angle of attack, RTO MP-069; 2001.
53. L.W. Traub Prediction of vortex breakdown and longitudinal charateristics of swept slender planforms J Aircraft 34 1997 3
54. W.H. Wentz Jr., and D.L. Kohlman Vortex breakdown on slender sharp-edged wings J Aircraft 8 1971 3
55. Pelletier A, Nelson RC. Factors influencing vortex breakdown over 70° delta wings. AIAA Paper 95-3469; 1995.
56. Guglieri G, Onerato M, Quagliotti FB. Vortex breakdown study on a 65° delta wing tested in static and dynamic conditions. In: Proceedings of the 18th international congress of aeronautical sciences. ICAS-92-4.10.2; 1992.
57. Lawford JA, Beauchamp AR. Low-speed wind-tunnel measirements on a thin sharp-edged delta wing with 70° leading-edge sweep, with particular reference to the position of leading-edge-vortex breakdown. R. & M. no. 3338, Aeronautical Research Council; 1963.
58. S.P. LeMay, S.M. Batill, and R.C. Nelson Vortex dynamics on a pitching delta wing J Aircraft 27 1990 2
59. Elle BJ. An investigation at low speed of the flow near the apex of thin delta wings with sharp leading edges. R. & M. no. 3176, Aeronautical Research Council; 1961.
60. J.J. Miau, R.C. Chang, J.H. Chou, and C.K. Lin Nonuniform motion of leading-edge vortex breakdown on ramp pitching delta wings J Aircraft 30 1992 7
61. Lowson MV, Riley AJ. Vortex breakdown control by delta wing geometry. AIAA Paper 94-3487; 1994.
62. L.W. Traub, B. Moeller, and O. Rediniotis Low-Reynolds-number effects on delta-wing aerodynamics J Aircraft 35 1998 15
63. Kowal HJ, Vakili AD. An investigation of unsteady vortex flow for a pitching-rolling 70° delta wing. AIAA Paper 98-0416; 1998.
64. Payne FM. The structure of leading edge vortex flows including vortex breakdown. Ph.D. thesis, University of Notre Dame; 1987.
65. McKernan JF, Nelson RC. An investigation of the breakdown of the leading edge vortices on a delta wing at high angles of attack. AIAA Paper 83-2114; 1983.
66. Brown CE, Michael Jr. WH. On slender delta wings with leading-edge separation. NACA TN-3430; 1955.
67. Smith JHB. Improved calculations of leading-edge separation from slender, thin, delta wings. In: Proceedings of the Royal Aeronautical Society A, vol. 306; 1968.
68. Jobe CE. Vortex Breakdown Location over 65° Delta wings: empiricism and experiment. AIAA Paper 98-2526, 1998.
69. Huang XZ, Hanff ES, Jobe CE. A critical assessment and requirement for ground testing on vortex breakdown locations over delta wings. In: Advanced flow management/part a: vortex flow and high angle of attack. RTO MP-069; 2001.
70. M.V. Lowson Visualization measurements of vortex flows J Aircraft 28 1991 5
71. Gatlin GM, McGrath BE. Low-speed longitudinal aerodynamic charateristics through poststall for twenty-one novel planform shapes. NASA TP-3503; 1995.
72. Chu J, Luckring JM. Experimental surface pressure data obtained on 65° delta wing across reynolds number and Mach number ranges. NASA TM-4645; 1996.
73. Loeser T. Oscillating 65° delta wing, experimental. In: verification and validation data for computational unsteady aerodynamics. RTO TR-026; 2000.
74. Ashill PR, Fulker JL, Simmons MJ, Betts CJ. Flow features of highly swept wings at subsonic and supersonic speeds. In: 17th international congress of aernautical sciences. ICAS-90-3.9.1; 1990.
75. Verhaagen NG, Jenkins LN, Kern SB, Washburn AE. A study of the vortex flow over a 76/40-deg double-delta wing. AIAA paper 95-0650. 1995.
76. Gonzalez HA, Erickson GE, McLachlan BG, Bell JH. Effects of various fillet shapes on a 76/40 double delta wing from Mach 0.18 to 0.7. In: Advanced flow management/part A: vortex flow and high angle of attack. RTO MP-069; 2001.
77. M.E. Beyers Interpretaion of experimental high-alpha aerodynamics - implications for flight prediction J Aircraft 32 1995 2
78. P.J. Lamont Pressures around an inclined ogive cylinder with laminar, transitional or turbulent separation AIAA J 20 1982 1
79. Kramer BR, Malcolm GN, Suárez CJ, James KD. Pressure distributions around an F/A-18 in static and rotary flow fields, with forebody vortex control. AIAA Paper 94-1828; 1994.
80. Keener ER. Flow-separation patterns on symmetric forebodies. NASA TM-86016; 1986.
81. D.I.A. Poll On the effects of boundary-layer transition on a cylindrical afterbody at incidence in low-speed flow Aeronaut J 89 1985
82. Polhamus EC. A review of some reynolds number effects related to bodies at high angles of attack. NASA CR-3809; 1984.
83. Walchli LA, Moorhouse DJ. Forebody vortex control. In: Advances in flight testing. AGARD-CP-593; 1996.
84. Hall RM. Influence of Reynolds number on forebody side forces for 3.5-diameter tangent-ogive bodies. AIAA Paper 87-2274; 1987.
85. Champigny P. Reynolds number effect on the aerodynamic characteristics of an ogive-cylinder at high angles of attack. AIAA Paper 84-2176; 1984.
86. A.H. Tajfar, and P.J. Lamont Sideslip behaviour of elliptic cross-sectional forebodies at high angle of attack J Aircraft 34 1997 4
87. Visintini L. Reynolds number simulation in high-alpha tests. In: Cooperative programme on dynamic wind tunnel experiments for manoeuvring aircraft. AGARD-AR-305. 1996.
88. Erickson GE. Wind tunnel investigation of the interaction and breakdown characteristics of slender-wing vortices at subsonic. Transonic and supersonic speeds. NASA TP-3114; 1991.
89. J.M. Délery Aspects of vortex breakdown Prog Aerospace Sci 30 1994 1