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Cone cavity flow at M = 8·2 with injection of air and helium

Published online by Cambridge University Press:  04 July 2016

F. Bellone  and
J. L. Stollery
F. Bellone
Affiliation:
College of Aeronautics, Cranfield University, Bedford, UK
J. L. Stollery
Affiliation:
College of Aeronautics, Cranfield University, Bedford, UK
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Abstract

An experimental investigation of cone cavity flow at M = 8·2 with injection of air and helium has been performed in the Cranfield University gun tunnel. The cone used had a 10° semi-angle and incorporated an annular cavity. The boundary layer ahead of the cavity was laminar. The study concentrated on the effects of increasing the mass injected into the cavity.

With no injection the external flow bridged the cavity. A shock wave and a pressure peak occurred at the rear face corner. By injecting gas, this pressure peak was decreased in intensity and a shock wave was formed at the front face corner. As the mass injected was increased, the shocks initially formed at the front and rear face corners were shifted upstream from their initial positions and boundary layer separation occurred ahead of the cavity. For the highest mass flow rate injected, the pressure peak at the rear face corner was very small. The cavity flow was never more than mildly unsteady.

Type
Research Article
Information
The Aeronautical Journal , Volume 103 , Issue 1029 , November 1999 , pp. 529 - 535
Copyright
Copyright © Royal Aeronautical Society 1999 

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