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Aerodynamic characteristics of delta wing–body combinations at high angles of attack

Published online by Cambridge University Press:  04 July 2016

P. R. Viswanath  and
S. R. Patil
P. R. Viswanath
Affiliation:
Experimental Aerodynamics Division, National Aerospace Laboratories, Bangalore, India
S. R. Patil
Affiliation:
Experimental Aerodynamics Division, National Aerospace Laboratories, Bangalore, India
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Abstract

An experimental study investigating the aerodynamic characteristics of generic delta wing-body combinations up to high angles of attack was carried out at a subsonic Mach number. Three delta wings having sharp leading edges and sweep angles of 50°, 60° and 70° were tested with two forebody configurations providing a variation of the nose fineness ratio. Measurements made included six-component forces and moments, limited static pressures on the wing lee-side and surface flow visualisation studies. The results showed symmetric flow features up to an incidence of about 25°, beyond which significant asymmetry was evident due to wing vortex breakdown, forebody vortex asymmetry or both. At higher incidence, varying degrees of forebody-wing vortex interaction effects were seen in the mean loads, which depended on the wing sweep and the nose fineness ratio. The vortex breakdown on these wings was found to be a gradual process, as implied by the wing pressures and the mean aerodynamic loads. Effects of forebody vortex asymmetry on the wing-body aerodynamics have also been assessed. Comparison of Datcom estimates with experimental data of longitudinal aerodynamic characteristics on all three wing-body combinations indicated good agreement in the symmetric flow regime.

Type
Research Article
Information
The Aeronautical Journal , Volume 98 , Issue 975 , May 1994 , pp. 159 - 170
Copyright
Copyright © Royal Aeronautical Society 1994 

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References

1. Stanbrook, A. and Squire, L.C. Possible types of flows at swept leading edges, Aeronaut Q, 1964,15, (1), pp 72–82.Google Scholar
2. Seshadri, S.N. and Narayan, K.Y. Possible types of flow on lee-surface of delta wings at supersonic speeds, Aeronaut J, 1988, pp 185–199.Google Scholar
3. Miller, D.S. and Wood, M.W. Lee-side flow over delta wings at supersonic speeds, Nasa TP-2430, 1985.Google Scholar
4. Earnshaw, P.B. and Lawford, J.A. Low Speed Wind-Tunnel Experiments on a Series of Sharp-Edged Delta Wings, ARC R & M 3424, 1964.Google Scholar
5. Sutton, E.P. Some Observations of the Flow Over a Delta Winged Model with 55° Leading Edge Sweep at Mach Numbers between 0·4 and 1·8, ARC R&M 3190, 1960.Google Scholar
6. Hoeijmakers, H.W.M., Vaatstra, W. and Verhaagen, N.G. Vortex flow over delta and double delta wings, J Aircr, 1983, 20, (3), pp 825–831.Google Scholar
7. Wood, R.M. and Miller, D.S. Fundamental aerodynamic characteristics of delta wings with leading-edge vortex flows, J Aircr, 1985, 22, (6), pp 479–485.Google Scholar
8. Wood, R.M., Byrd, J.E. and Wesselmann, G.F. Influence of airfoil geometry on delta wing leading-edge vortices and vortex-induced aerodynamics at supersonic speeds, Nasa TP-3105, 1992.Google Scholar
9. Seshadri, S.N. and Narayan, K.Y. Shock-induced separated flows on the lee-side surface of delta wings, Aeronaut J, 1987, 91, (903), pp 128–141.Google Scholar
10. Erickson, G.E. Wind Tunnel Investigation of the Interaction and Breakdown Characteristics of Slender-Wing Vortices at Subsonic, Transonic and Supersonic Speeds, Nasa TP-3114, 1991.Google Scholar
11. Parker, A.G. Aerodynamic characteristics of slender wings with sharp leading edges — a review, J Aircr, March 1976, 13, (3), pp 161–168.Google Scholar
12. Szodruch, J.G. and Peake, D.J. Leeward flow over delta wings at supersonic speeds, Nasa TM-81187, 1980.Google Scholar
13. Narayan, K.Y. and Seshadri, S.N. Vortical flows on the lee surface of delta wings, Symp. Transonicum III, Zierep, J., Oertel, H., (Eds), Springer-Verlag Berlin Heidelberg, 1989.Google Scholar
14. Lee, M. and Ho, C.M. Lift force of delta wings, App Mech Reviews, 1990, 43, (9), pp 209–221.Google Scholar
15. Hoeijmakers, H.W.M. Numerical simulation of vortical flow, VKI Lecture Series 1986-08, 1986.Google Scholar
16. Rizzi, A. and Purcell, C.J. On the computation of transonic leading-edge vortices using the Euler equations, J Fluid Mech, 1987, 181, pp 163–195.Google Scholar
17.Murman, E.M., Goodsell, A.M. and Malecki, R.E. Transonic vortical flow, Symp Transonicum II, Zierep, J. and Oertel, H. (Eds), Springer-Verlag Berlin Heidelberg, 1989.Google Scholar
18. Skow, A.M., Titriga, A. and Moore, W.A. Forebody/wing vortex interactions and their influence on departure and spin resistance, AGARD CP-247, 1978.Google Scholar
19. Fox, C.H. Jr, Subsonic longitudinal and lateral-directional static aerodynamic characteristics of a general research fighter model employing a strake-wing concept, Nasa TM-74071, 1978.Google Scholar
20. Luckrlng, J.M. Subsonic longitudinal and lateral aerodynamic characteristics for a systematic series of strake-wing configurations, Nasa TM-78642, 1979.Google Scholar
21. Hummel, D., John, H. and Staudacher, W. Aerodynamic characteristics of wing body combinations at high angles of attack, Icas paper 84-2.7.1, 1984.Google Scholar
22. Manor, D. Low Aspect Ratio Wing/Body Vortex Interaction at Large Angles of Pitch and Yaw, PhD Dissertation, Wichita State University, 1983.Google Scholar
23. Erickson, G.E. and Brandon, J.M. On the non-linear aerodynamic and stability characteristics of a generic chine-forebody slender-wing fighter configuration, AIAA Paper 87-2617, 1987.Google Scholar
24. Rae, W.J. Jr and Pope, A. Low Speed Wind Tunnel Testing, John Wiley & Sons, 1984.Google Scholar
25. Bucciantini, G., Desilverstro, R. and Fornaiser, L. A survey of recent high angles of attack wind tunnel testing at Aeritalia, AGARD CP-247, 1979.Google Scholar
26. Patil, S.R. and Sridharan, R. Wind tunnel wall corrections to experimental data on wing-body combinations at high angles of attack, NAL PD EA 8908, 1989.Google Scholar
27. Viswanath, P.R. and Patil, S.R. Aerodynamic characteristics of delta wing-body combinations at high angles of attack, NAL PD EA 9205, 1992.Google Scholar
28. Dietz, W.E. and Alstatt, M.C. Experimental investigation of support interference on an ogive cylinder at high incidence, J Spacecr Rockets, 1979, 16, (3), pp 67–68.Google Scholar
29. Canning, T.N. and Nielsen, J.N. Influence of support systems on the aerodynamics of an inclined ogive cylinder, J Spacecr Rockets, 1982, 19, (3), pp 205–210.Google Scholar
30. Hunt, B.L. Asymmetric vortex forces and wakes, AIAA paper 82-1336, 1982.Google Scholar
31. Chapman, G.T. and Yates, L.A. Topology of flow separation on three-dimensional bodies, App Mech Reviews, 1991, 44, (7), pp 329–345.Google Scholar
32. Keener, E.R., Chapman, G.T. and Kruse, R.L. Effects of Mach number and afterbody length on aerodynamic side forces at zero side-slip on symmetric bodies at high angles of attack, AIAA Paper 76-66, 1976.Google Scholar
33. Chapman, G.T., Keener, E.R. and Malcum, G.N. Asymmetric aerodynamic forces on aircraft forebodies at high angles of attack — some design guides, AGARD Specialists Meeting on “Stall/Spin Problems of Military Aircraft”, Paper No 16, Belgium, 1976.Google Scholar
34. Keener, E.R. and Chapman, G.T. Onset of aerodynamic side forces at zero side slip on symmetric bodies at high angles of attack, AIAA Paper 74-770, 1974.Google Scholar
35. Seshadri, S.N. and Narayan, K.Y. Private Communication.Google Scholar
36. Schemensky, R.T. Development of an empirically based computer program to predict aerodynamic characteristics of aircraft, AFFDL-TR-73-144, 1, 1973.Google Scholar
37. USAF Stability and Control DATCOM, 7, 1968.Google Scholar