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Hypersonic control flapeffectiveness

Published online by Cambridge University Press:  04 July 2016

D. Kumar  and
J. L. Stollery
D. Kumar
Affiliation:
College of Aeronautics, Cranfield University, Cranfield, UK
J. L. Stollery
Affiliation:
College of Aeronautics, Cranfield University, Cranfield, UK
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Summary

The effects of flap deflection, configuration incidenceand leading edge bluntness on boundary layerseparation and transition have been studiedexperimentally. A quasi two-dimensional flat plateequipped with a full span trailing edge control flaphas been employed for these tests.

The studies have been carried out in a hypersonic guntunnel at M∞ = 8·2 and Re∞/cm= 9·0 × 104. The flap deflection anglesstudied were in the range 0° ≤ β ≤ 30°. Theincidence range was from zero to α = 10° (positive αis nose down). Leading edge bluntness effects weresimulated by the introduction of a hemi-cylindricalleading edge.

The flow structure was studied using high speedSchlieren photography as well as surface pressureand heat transfer measurements. Liquid crystals wereemployed to study the threedimensionality of theflow structure for selected configurations.Analytical theories have been developed to estimatethe flap pressure and heat transfer levels for thesharp and blunt configurations. These are comparedagainst experimental measurements.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 100 , Issue 996 , July 1996 , pp. 197 - 208
Copyright
Copyright © Royal Aeronautical Society 1996 

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References

1. Stetson, K.F. Nose bluntness effects on cone frustum boundary layer transition in hypersonic flow, AIAA 83-1763, 1983.Google Scholar
2. Ericsson, L.E. Effects of nose bluntness and cone angle on slender vehicle transition, AIAA J, October 1988, 26, (10).Google Scholar
3. Jillie, D.W. and Hopkins, E.J. Effect of Mach number, leading edge bluntness and sweep on boundary layer transition on a flat plate, NASATN-D 1071, 1961.Google Scholar
4. Reshotko, E. and Khan, M.M.S. Stability of a laminar boundary layer on a blunted flat plate in supersonic flow-laminar-turbulent transition, IUTAM Symposium, Stuttgart, September 1979, pp 189-200.Google Scholar
5. Sanator, R.J., Boccio, J.L. and Shamshins, D. Effects of bluntness on hypersonic two-dimensional inlet type flows, NASA CR-1145, 1968.Google Scholar
6. Edwards, C.L.W. and Anders, J.B. LOW density, leading edge bluntness and ablation effects on wedge induced laminar boundary layer separation at moderate enthalpies in hypersonic flows, NASA TND-4829, 1968.Google Scholar
7. Vermeulen, J.P. and Simeonides, G. Parametric study of shock- wave/boundary layer interactions over 2-D compression corners at Mach6,VKITN-181, 1992.Google Scholar
8. Townsend, J.C. Effects of leading edge bluntness and ramp deflection angle on laminar boundary layer separation in hypersonic flow, NASA TN-D 3290, 1966.Google Scholar
9. Coet, M.C., Delery, J. and Chantez, B. Experiments on shock- wave-boundary layer interaction at high Mach number with entropy layer effect, IUTAM Symposium, Marseille, 1992.Google Scholar
10. Holden, M. Experimental studies in shockwave-boundary layer interactions, AGARD AG-203, 1975.Google Scholar
11. Stollery, J.L. and Coleman, G.T. A correlation between pressure and heat transfer distributions at supersonic and hypersonic speeds, Aeronaut Q, Nov 1975, 26, (5), pp 304–312.Google Scholar
12. AMES RESEARCH STAFF Equations, tables and charts for compressible flows, NACA-R-1135, 1953.Google Scholar
13. Kumar, D. and Stollery, J.L. The effect of leading edge bluntness on control effectiveness at hypersonic speeds, 19th International Symposium on Shock Waves, July 1993, Marseille, 1993.Google Scholar
14. Lukasiewicz, J. Hypersonic flow blast analogy, AEDC TN-61-158, 1961.Google Scholar
15. Richards, G. High Speed Flow Over Two-Dimensional and Axi-Sym- metric Bodies, PhD Thesis, Cranfield Institute of Technology, 1978.Google Scholar
16. Anderson, J.D. Hypersonic and High Temperature Gas Dynamics, McGraw Hill, 1989.Google Scholar
17. Elfstrom, G.M. Turbulent hypersonic flow at a wedge-compression corner, J Fluid Mech, 1972, 53, (1), pp 113–127.Google Scholar
18. Stone, H.W. The leading edge effects on the laminar flat plate boundary layer and the aerodynamic heating at Mach 10-4, NASA TN-D5160, 1969.Google Scholar
19. Needham, D.A. Laminar Separation in Hypersonic Flows, PhD thesis, University of London, 1965. (See also Needham and Stollery AIAA Paper 66-455, 1966).Google Scholar
20. Inoer, G.R. Scaling of incipient separation in high speed laminar flows, AIAA-93-3435, 1993.Google Scholar
21. Hayes, W.D. and Probstein, R.F. Hypersonic Flow Theory Volume I —Inviscid Flows, Academic Press, 1966.Google Scholar