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Calculated Pressure Distributions and Shock Shapes on Thick Conical Wings at High Supersonic Speeds

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

In recent papers Messiter and Hida have proposed a first-order correction to simple Newtonian theory for the pressure distributions on the lower surfaces of lifting conical bodies with detached shocks. The method involves the solution of an integral equation which Messiter solved numerically for thin delta wings, while Hida gave an approximate solution for thick wings with diamond and bi-convex cross-sections. It is shown in the present paper that Hida’s approximate solutions give poor agreement with experiment, and a series of more precise numerical solutions of the equation are given for wings with diamond cross-sections. The pressures, and shock shapes, obtained from these solutions are in very good agreement with experiment at Mach numbers as low as 4·0.

The method has also been extended to Nonweiler wings at off-design when the shock wave is detached from the leading edges. Again the agreement with experiment is good provided the integral equation is solved numerically.

Type
Research Article
Information
Aeronautical Quarterly , Volume 18 , Issue 2 , May 1967 , pp. 185 - 206
Copyright
Copyright © Royal Aeronautical Society. 1967

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References

1. Küchemann, D. Hypersonic aircraft and their aerodynamic problems. Progress in Aeronautical Sciences, Vol. 6. Pergamon Press, 1965.Google Scholar
2. Messiter, A. F. Lift of slender delta wings according to Newtonian theory. AIAA Journal, Vol. 1 p. 794, 1963.CrossRefGoogle Scholar
3. Hida, K. Thickness effects on the force of slender wings in hypersonic flow. AIAA Journal, Vol. 3 p. 427, 1965.CrossRefGoogle Scholar
4. Squire, L. C. Pressure distributions and flow patterns at M=4-0 on some delta wings. ARC R & M 3373, 1963.Google Scholar
5. Squire, L. C. Pressure distributions and flow patterns on some conical shapes with sharp edges and symmetrical cross-sections at M=40. ARC R & M 3340, 1962.Google Scholar
6. Peckham, D. H. Pressure distribution measurements on a series of slender delta body shapes at Mach numbers of 6-85 and 860. ARC Current Paper 791, 1964.Google Scholar
7. Collis, D. A hypersonic wind tunnel study of a thick delta wing. Australian Research Laboratories Note ARL/A232, 1964.Google Scholar
8. Nonweiler, T. R. F. Delta wings of shapes amenable to exact shock wave theory. Journal of the Royal Aeronautical Society, Vol. 67 p. 39, 1963.CrossRefGoogle Scholar