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Hypersonic large-deflection similitude for oscillating delta wings

Published online by Cambridge University Press:  04 July 2016

Kunal Ghosh
Kunal Ghosh*
Affiliation:
Department of Aeronautical Engineering, IIT, Kanpur, India
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Abstract

A similitude has been obtained for delta wings with attached leading edge shock at large incidence in hypersonic flow. A strip theory in which flow at a spanwise location is two-dimensional has been developed. This combines with the similitude to lead to a piston theory which gives closed form solutions for unsteady derivatives in pitch and roll. The derivatives in pitch are independent of and the roll damping derivative varies linearly with the aspect ratio. Substantially the same results as the theory of Liu and Hui are obtained with remarkable computational ease.

Type
Research Article
Information
The Aeronautical Journal , Volume 88 , Issue 878 , October 1984 , pp. 357 - 361
Copyright
Copyright © Royal Aeronautical Society 1984 

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References

1. Cole, J. D. and Brainerd, J. J. Slender wings at high angles of attack in hypersonic flow, ARS Reprint 1980-61,1961.Google Scholar
2. Ghosh, K. A new similitude for aerofoils in hypersonic flow, Proc of the 6th Canadian Congress of Applied Mechanics, Vancouver, 29thMay- 3rd June 1977,685–686.Google Scholar
3. Ghosh, K. and Mistry, B. K. Large incidence hypersonic similitude and oscillating non-planar wedges, AIAA Journal, August 1980,18,8,1004–1006.Google Scholar
4. Ghosh, Kunal. Hypersonic large-deflection similitude for quasi-wedges and quasi-cones, The Aeronautical Journal, March 1984, 88,873,70–76.Google Scholar
5. Hayes, W. D. and Probstein, R. F. Hypersonic flow theory, Academic Press, New York, London, 1966,1.Google Scholar
6. Hui, W. H. Supersonic and hypersonic flow with attached shock waves over delta wings, Proc of Royal Society, London, 1971, A. 325,251–268.Google Scholar
7. Hui, W. H. and Hemdan, H. T. Unsteady hypersonic flow over delta wings with detached shock waves, AIAA Journal, April 1976,14,505–511.Google Scholar
8. Hui, W. H. and Tobak, Murray. Unsteady Newton-Busemann flow theory — Part I: Airfoils, AIAA Journal, March 1981,19, 311; Unsteady Newton-Busemann flow theory — Part II: Bodies of revolution, AIAA Journal, October 1981,19,1272.Google Scholar
9. Hui, W. H., Platzer, M. F. and Youroukos, E. Oscillating supersonic/hypersonic wings at high incidence, AIAA Journal, March 1982,20,299–304.Google Scholar
10. Lighthill, M. J. Oscillating airfoil at high Mach numbers, Journal of Aeronautical Sciences, 1953,20,402–406.Google Scholar
11. Liu, D. D. and Hui, W. H. Oscillating delta wings with attached shock waves, AIAA Journal, June 1977,15,6,804–812.Google Scholar
12. Malmuth, N. D. Hypersonic flow over a delta wing of moderate aspect ratio, AIAA Journal, 1966,4,555–556.Google Scholar
13. Messiter, A. F. Lift of slender delta wings according to Newtonian theory, AIAA Journal, 1963,1,794–802.Google Scholar
14. Miles, J. W. Unsteady flow at hypersonic speeds, Hypersonic Flow, Butterworths Scientific Publications, London, 1960, 185–197.Google Scholar
15. Orlik-Ruckemann, K. J. Dynamic stability testing of aircraft-needs versus capabilities, Progress in the Aerospace Sciences, Academic Press, N. Y., 1975,16,431–447.Google Scholar
16. Pike, J. The pressure on flat and anhydral delta wings with attached shock waves, The Aeronautical Quarterly, November 1972, XXIII, Part 4,253–262.Google Scholar
17. Squire, L. C. Calculated pressure distributions and shock shapes on conical wings with attached shock waves, The Aeronautical Quarterly, February 1968, XIX, 31–50.Google Scholar
18. Sychev, V. V. Three-dimensional hypersonic gas flow past slender bodies at high angles of attack, Journal of Applied Mathematics and Mechanics, 1960,24,296–306.Google Scholar
19. Townend, L. H. Some design aspects of space shuttle orbitors, RAE TR 70139,1970.Google Scholar