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Buffeting tests in a cryogenicwindtunnel

Published online by Cambridge University Press:  04 July 2016

D. G. Mabey,
R. P. Boyden and
W. G. Johnson
D. G. Mabey
Affiliation:
Department of Aeronautics, Imperial College, London
R. P. Boyden
Affiliation:
Nasa Langley, USA
W. G. Johnson
Affiliation:
Nasa Langley, USA
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Summary

Measurements of wing buffeting, using root straingauges, were made in the Nasa Langley 0-3 mcryogenic windtunnel to refine techniques which willbe used in larger cryogenic facilities such as theUnited States National Transonic Facility (NTF) andthe European Transonic Windtunnel (ETW). Thequestions addressed included the relative importancevariations in frequency parameter and Reynoldsnumber, the choice of model material (consideringboth stiffness and damping) and the effects ofstatic aeroelastic distortion.

The main series of tests was made on three half modelsof slender 65° delta wings with a sharp leadingedge. The three delta wings had the same planformbut widely differing bending stiffnesses andfrequencies (obtained by varying both the materialand the thickness of the wings). It was known thatthe steady flow on this configuration would beinsensitive to variations in Reynolds number. Onthis wing at vortex breakdown the spectrum of theunsteady excitation is unusual, having a sharp peakat particular frequency parameter.

Additional tests were made on one unswept half-wing ofaspect ratio 1·5 with an NPL 9510 aerofoil section,known to be sensitive to variations in Reynoldsnumber at transonic speeds. The test Mach numberswere M = 0·21 and 0·35 for the delta wings and to M= 0·30 for the unswept wing. On this wing theunsteady excitation spectrum is fairly flat (as onmost wings). Hence correct representation of thefrequency parameter is not particularlyimportant.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 99 , Issue 981 , January 1995, pp. 1 - 14
Copyright
Copyright © Royal Aeronautical Society 1995 

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