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Three-dimensional wings in hypersonic flow

Published online by Cambridge University Press:  29 March 2006

R. Hillier
R. Hillier
Affiliation:
Engineering Department, Cambridge University Present address: Central Electricity Research Laboratories, Leatherhead, Surrey.
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Abstract

Messiter's thin shock layer approximation for hypersonic wings is applied to several non-conical shapes. Two calculation methods are considered. One gives the exact solution for a particular three-dimensional geometry which possesses a conical planform and also a conical distribution of thickness superimposed upon a surface cambered in the chordwise direction. Agreement with experiment is good for all cases, including that where the wing is yawed. The other method is a more general approach whereby the solution is expressed as a correction to an already known conical flow. Such a technique is applicable to conical planforms with either attached or detached shocks but only to the non-conical planform for the region in the vicinity of the leading edge when the shock is attached.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 54 , Issue 2 , 25 July 1972 , pp. 305 - 337
Copyright
© 1972 Cambridge University Press

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References

Antonov, A. M. & Hayes, W. D. 1966 Calculation of the hypersonic flow about blunt bodies J. Appl. Math. Mech. 30, 421–427.Google Scholar
Cole, J. D. & Brainerd, J. J. 1962 Slender wings at high angles of attack in hypersonic flows. In Hypersonic Flow Research (ed. F. R. Riddell), pp. 321–343. Academic.
Hayes, W. D. & Probstein, R. F. 1966 Hypersonic Flow Theory. Part 1. Inviscid Flows. Academic.
Hida, K. 1965 Thickness effects on the force of slender delta wings in hypersonic flow A.I.A.A. J. 3, 427–433.Google Scholar
Hillier, R. 1970a The effects of yaw on conical wings at high supersonic speeds. Aero. Quart. 21, 199–210.Google Scholar
Hillier, R. 1970b Some applications of thin shock layer theory to hypersonic wings. Ph.D. dissertation, University of Cambridge.
Hillier, R. 1971 Pressure distributions at M = 3·51 and at high incidences on four wings with delta planform. Aero. Res. Counc. Current Paper, no. 1198.Google Scholar
Melnik, R. E. & Scheuing, R. A. 1962 Shock layer structure and entropy layers in hypersonic conical flows. In Hypersonic Flow Research (ed. F. R. Riddell), pp. 379–420. Academic.
Messiter, A. F. 1963 Lift of slender delta wings according to Newtonian theory A.I.A.A. J. 1, 794–802.Google Scholar
Roe, P. L. 1970 Aerodynamic problems of hypersonic aircraft. Von Kármán Institute short course.
Roe, P. L. 1971 A simple treatment of the attached shock layer on a delta wing. R.A.E. unpublished work.Google Scholar
Squire, J. C. 1966 Calculated pressure distributions and shock shapes on thick conical wings at high supersonic speeds Aero. Quart. 18, 185–206.Google Scholar
Squire, L. C. 1968a Calculation of pressure distributions on lifting conical wings with application to the off design behaviour of wave riders. AGARD Conf. Proc. p. 30.Google Scholar
Squire, L. C. 1968b Calculated pressure distributions and shock shapes on conical wings with attached shock waves. Aero. Quart. 19, 31–50.Google Scholar
Squire, L. C., Jones, J. G. & Stanbrook, A. 1963 An experimental investigation of the characteristics of some plane and cambered 65° delta wings at Mach numbers from 0·7 to 2·0. Aero. Res. Counc. R. & M. no. 3305.Google Scholar
Woods, B. A. 1970 Hypersonic flow with attached shock waves over delta wings Aero. Quart. 21, 379–399.Google Scholar