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Hypersonic large-deflection similitude for oscillating delta wings

Published online by Cambridge University Press:  04 July 2016

Kunal Ghosh
Kunal Ghosh*
Affiliation:
Department of Aeronautical Engineering, IIT, Kanpur, India
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Abstract

A similitude has been obtained for delta wings with attached leading edge shock at large incidence in hypersonic flow. A strip theory in which flow at a spanwise location is two-dimensional has been developed. This combines with the similitude to lead to a piston theory which gives closed form solutions for unsteady derivatives in pitch and roll. The derivatives in pitch are independent of and the roll damping derivative varies linearly with the aspect ratio. Substantially the same results as the theory of Liu and Hui are obtained with remarkable computational ease.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 88 , Issue 878 , October 1984, pp. 357 - 361
Copyright
Copyright © Royal Aeronautical Society 1984 

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