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The impact of a shock-wave on a thin two-dimensional aerofoil moving at supersonic speed

Published online by Cambridge University Press:  28 March 2006

J. L. Smyrl
J. L. Smyrl
Affiliation:
Department of Mathematics, Royal College of Science and Technology, Glasgow
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Abstract

The pressure field is found in closed analytic form for the region behind an arbitrary plane shock, which has encountered a thin aerofoil moving at supersonic speed. The solution may be used for wedges at small incidence to the air-flow around them, and for wedges yawed with respect to the shock plane through angles up to a limiting value which always exceeds 67·8°. The pressure distribution on the surface of a wedge is calculated in a number of examples illustrating separately the effects of shock strength, wedge speed, and angle of yaw.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 15 , Issue 2 , February 1963 , pp. 223 - 240
Copyright
© 1963 Cambridge University Press

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References

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