The Hypersonic Source Flow Past Wedges and Cones-Reference-Cited by-同舟云学术

The Hypersonic Source Flow Past Wedges and Cones

Published:1971-11 Issue:4 Volume:22 Page:327-345
ISSN:0001-9259
Container-title:Aeronautical Quarterly
language:en
Short-container-title:Aeronautical Quarterly

Author:

Gorgui M. A.

Abstract

SummaryTo study the effects of flow non-uniformities on the hypersonic flow past test bodies, perturbation analysis is applied to the hypersonic source flow past wedges and cones. In both cases it is shown that the effects of the source flow on the shock shape and velocity are small, while effects on the pressure and density are large. Curves are presented for various values of the Mach number from which these effects can be estimated.

Publisher

Cambridge University Press (CUP)

Subject

General Engineering

Reference9 articles.

1. George A. R. Hypersonic flow over a wedge with upstream non-uniformities and variable wedge angle. Gas Dynamic Laboratory, Princeton University, Report 695, 1964.

2. Theory of a thin wing in a shear flow

3. The fundamental solution for small steady three-dimensional disturbances to a two-dimensional parallel shear flow

4. Savage S. B. Effects of a source-type hypersonic free stream on the flow field about an axisymmetric cone. Republic Aviation Corporation Report 2243, 1964.

5. Meyer R. F. The flow about a particular class of plane and axisymmetric ogive in a hypersonic source flow. National Research Council of Canada Report LR-408, 1964.

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1. Calculation of radial supersonic gas flow past sharp-nosed cones;Computational Mathematics and Modeling;1996

2. Supersonic radial flow past sharp-nosed cones;Fluid Dynamics;1994-04

3. Linearized theory of axisymmetric hypersonic source flow past bodies of revolution;Journal of Fluid Mechanics;1976-01-13

4. Inviscid Hypersonic Source Flow, over Slender Power-Law Bodies;Aeronautical Quarterly;1975-08

5. Effects of Upstream Unsteadiness on Hypersonic Flow past a Wedge;Physics of Fluids;1972