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The Effects of Recessed Lower Surface Shape on the Lift and Drag of Conical Wings at High Incidence and High Mach Number

Published online by Cambridge University Press:  07 June 2016

L C Squire*
Affiliation:
Cambridge University Engineering Department
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Summary

For lifting re-entry there may be advantages in using wings which give as high a lift coefficient as possible at the design value of the lift/drag ratio. This paper presents the results of an experimental and theoretical study of wings with recessed lower surfaces designed to give high values of CL. The calculations show that a wide range of wing shapes can be found that give values of CL which are much larger than those on a flat wing with the same lift/drag ratio.

Type
Research Article
Copyright
Copyright © Royal Aeronautical Society. 1975

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References

1 Townend, L H Some design aspects of space shuttle orbiters. Progress in Aerospace Sciences, Vol 13, pp 81136, Pergamon, 1972.Google Scholar
2 Squire, L C A comparison of the lift of flat delta wings and waveriders at high angles of incidence and high Mach number. Ingenieur-Archiv, Vol 40, pp 339352, 1971.Google Scholar
3 Shanbhag, V V Numerical studies on hypersonic delta wings with detached shock waves. ARC Current Paper 1277, 1974.Google Scholar
4 Squire, L C Some extensions of thin-shock-layer theory. Aeronautical Quarterly, Vol XXV, pp 113, February 1974.Google Scholar
5 Bazzhin, A P Calculation of the flow past plane triangular wings at large angles of attack. Iz AN SSSR Mekhanika Zhidkosti i Gaza, Vol 2, pp 119123, 1967.Google Scholar
6 Bashkin, V A Experimental study of flow about flat delta wings at M = 5 and angles of attack from 0 to 70°. Izv AN SSSR Mekhanika Zhidkosti i Gaza, Vol 2, pp 102108, 1967.Google Scholar