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Hypersonic flow with attached shock waves over plane delta wings

Published online by Cambridge University Press:  11 April 2006

B. A. Woods  and
C. B. G. Mcintosh
B. A. Woods
Affiliation:
Department of Mathematics, University of Canterbury, Christchurch, New Zealand
C. B. G. Mcintosh
Affiliation:
Mathematics Department, Monash University, Clayton, Victoria 3168, Australia
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Abstract

A new form is given for the general solution to the thin-shock-layer equations for the flow over a nearly plane delta wing. Using this, the solution described conjecturally by Hayes & Probstein for symmetrical flow with attached shock waves over a plane delta wing is realized numerically. The flow construction devised for this purpose is applied also to yawed flows. The solutions obtained are found to agree moderately well with the results of numerical calculations from the full equations, but contain a number of anomalous features characteristic of the thin-shock-layer approximation.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 79 , Issue 2 , 22 February 1977 , pp. 361 - 377
Copyright
© 1977 Cambridge University Press

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References

Babaev, D. A. 1963a Numerical solution of the problem of flow around the lower surface of a delta wing. A.I.A.A. J. 1, 2224–2231.Google Scholar
Babaev, D. A. 1963b Flow about a triangular wing for large values of. M. U.S.S.R. Comp. Math. & Math. Phys. 3, 528–532.Google Scholar
Hayes, W. D. & Probstein, R. F. 1966 Hypersonic Flow Theory, vol. 1. Inviscid Flows, pp. 329–342. Academic.
Hui, W. H. 1971 Supersonic and hypersonic flow with attached shock waves over delta wings. Proc. Roy. Soc. A 325, 251–268.Google Scholar
Hui, W. H. 1973 Effect of yaw on supersonic and hypersonic flow over delta wings. Aero. J. 77, 299–301.Google Scholar
Klunker, E. B., South, J. C. & Davis, R. M. 1971 Calculation of nonlinear conical flows by the method of lines. N.A.S.A. Tech. Rep. TR R-374.Google Scholar
Malmuth, N. D. 1966 Hypersonic flow over a delta wing of moderate aspect ratio. A.I.A.A. J. 4, 555–556.Google Scholar
Malmuth, N. D. 1973 Pressure fields over hypersonic wing-bodies at moderate incidence. J. Fluid Mech. 59, 673–691.Google Scholar
Messiter, A. F. 1963 Lift of slender delta wings according to Newtonian theory. A.I.A.A. J. 1, 794–802.Google Scholar
Mises, R. von 1958 Mathematical Theory of Compressible Fluid Flow. Academic.
Roe, P. L. 1970 A simple treatment of the attached shock layer on a delta wing. Roy. Aircraft Est. Tech. Rep. no. 70246.Google Scholar
Squire, L. C. 1967 Calculated pressure distributions and shock shapes on thick conical wings at high supersonic speeds. Aero. Quart. 18, 185–206.Google Scholar
Squire, L. C. 1968 Calculated pressure distributions and shock shapes on conical wings with attached shock waves. Aero. Quart. 19, 31–50.Google Scholar
Squire, L. C. 1974 Some extensions of thin-shock-layer theory. Aero. Quart. 24, 1–13.Google Scholar
Stocker, P. M. & Mauger, F. E. 1962 Supersonic flow past cones of general cross-section. J. Fluid Mech. 13, 383–399.Google Scholar
Voskresenskii, G. P. 1968 Numerical solution of the problem of a supersonic gas flow past an arbitrary surface of a delta wing in the compression region. Izv. Akad. Nauk SSSR, Mekh. Zh. i Gaza, 4, 134–142.Google Scholar
Woods, B. A. 1970 Hypersonic flow with attached shock waves over delta wings. Aero. Quart. 21, 379–399.Google Scholar