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Calculated Pressure Distributions and Shock Shapes on Conical Wings with Attached Shock Waves

Published online by Cambridge University Press:  07 June 2016

L. C. Squire
L. C. Squire*
Affiliation:
Engineering Department, Cambridge University
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Summary

Recently Messiter has proposed a first-order correction to simple Newtonian theory for the pressure distribution on the lower (compression) surfaces of lifting conical bodies. Although the basic theory holds for bodies with and without attached shock waves, solutions have so far only been obtained for bodies with detached shocks. In the present paper an approximate method of applying the theory to bodies with attached shocks is given. In spite of the approximations involved the calculated shock shapes and pressure distributions are in good agreement with some exact solutions for flat wings, except near the incidence for shock detachment. Like the detached shock case, the present solution can be applied to Nonweiler wings in certain off-design conditions. The combined results for the detached shock and for the attached shock enable the off-design behaviour of Nonweiler wings to be discussed in a systematic manner.

Type
Research Article
Information
Aeronautical Quarterly , Volume 19 , Issue 1 , February 1968 , pp. 31 - 50
Copyright
Copyright © Royal Aeronautical Society. 1968

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References

1. Squire, L. C. Calculated pressure distribution and shock shapes on thick conical wings at high supersonic speeds. Aeronautical Quarterly, Vol. XVIII, p. 185, May 1967.Google Scholar
2. Messiter, A. F. Lift of slender delta wings according to Newtonian theory. AlAA Journal, Vol. 1, p. 794, 1963.Google Scholar
3. Babaev, D. A. Numerical solution of the problem of the supersonic flow past the lower surface of a delta wing. Translated from Russian in AlAA Journal, Vol. 1, p. 2224, 1963.Google Scholar
4. Crabtree, L. F. and Treadgold, D. A. Experiments on hypersonic lifting bodies. Fifth Congress of the International Council of the Aeronautical Sciences, 1966. ICAS Paper 66-24.Google Scholar
5. Squire, L. C. Pressure distributions and flow patterns at M = 4·0 on some delta wings. R & M 3373, 1963.Google Scholar
6. Squire, L. C. Charts for the calculation of pressure distributions on conical bodies at high supersonic speeds. To be published by AGARD.Google Scholar
7. Küchemann, D. Hypersonic aircraft and their aerodynamic problems. Progress in Aeronautical Sciences, Vol. 6. Pergamon Press, 1965.Google Scholar