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Shock phenomena in high speed aerodynamics: still a source of major concern

Part of: RAeS Lanchester Lecture Papers

Published online by Cambridge University Press:  04 July 2016

J. M. Délery
J. M. Délery*
Affiliation:
ONERA , 92190 Meudon, France
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Abstract

Shockwaves are present in a flow as soon as the Mach number becomes supersonic. Being viscous phenomena, Shockwaves are a source of drag which can be predominant when the Mach number is significantly higher than one. In supersonic air intakes, the production of entropy by shocks is felt as a loss in efficiency. At high Mach numbers, Shockwaves produce a considerable temperature rise leading to severe heating problems, complicated by real gas effects. The intersection - or interference - of two shocks gives rise to complex wave patterns containing slip-lines and associated shear layers whose impingement on a nearby surface can cause detrimental pressure and heat transfer loads. The impact of a Shockwave on a boundary layer is the origin of strong viscous interactions which remain a limiting factor in the design of transonic wings, supersonic air intakes, propulsive nozzles and compressor cascades. More effort is needed to improve prediction of these interactions and to devise new techniques to control such phenomena.

Information

Type
Lanchester lecture
Information
The Aeronautical Journal , Volume 103 , Issue 1019 , January 1999 , pp. 19 - 34
Copyright
Copyright © Royal Aeronautical Society 1999 

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