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Alleviation of shock oscillations in transonic flow by passive controls

Published online by Cambridge University Press:  04 July 2016

S. Raghunathan ,
D. E. Hall  and
D. G. Mabey
S. Raghunathan
Affiliation:
Queen's University of Belfast
D. E. Hall
Affiliation:
Queen's University of Belfast
D. G. Mabey
Affiliation:
Royal Aerospace Establishment, Bedford
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Abstract

Passive control experiments were made on an 18% thick biconvex aerofoil model in Mach number range giving shock oscillations and at a Reynolds number of 0.7 x 106 with fixed boundary layer transition. The control methods studied included a passive control of shock wave boundary layer interaction by a porous surface and a cavity, and a buffet breather made of holes connecting upper and lower surfaces of the aerofoil. The experiments show that the shock oscillations can be virtually eliminated by these methods. A physical explanation is given for the success of these passive controls.

Type
Research Article
Information
The Aeronautical Journal , Volume 94 , Issue 937 , September 1990 , pp. 245 - 250
Copyright
Copyright © Royal Aeronautical Society 1990 

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