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Design and performance of thin, circular arc, wind-tunnel turning vanes

Published online by Cambridge University Press:  03 February 2016

G. Johl ,
M. Passmore  and
P. Render
G. Johl
Affiliation:
Department of Aeronautical and Automotive Engineering, Loughborough University, Loughborough, UK
M. Passmore
Affiliation:
Department of Aeronautical and Automotive Engineering, Loughborough University, Loughborough, UK
P. Render
Affiliation:
Department of Aeronautical and Automotive Engineering, Loughborough University, Loughborough, UK
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Extract

Although test rig data exists for ¼ circle turning vanes, the actual performance of these vanes once installed in a wind tunnel, and the extent to which test rig results are replicated, is rarely known. This paper compares pressure loss coefficient and velocity profile data from a vane test module with measurements taken in the low speed wind tunnel described in Ref. 1.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1116 , February 2007 , pp. 115 - 118
Copyright
Copyright © Royal Aeronautical Society 2007 

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References

1. Johl, G.S., Passmore, M.A. and Render, P.M., Design methodology and performance of an indraft wind tunnel, Aeronaut J, September 2004, 108,(1087), pp 465–473.Google Scholar
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3. Collar, A.R; Some experiments with cascades of aerofoils, Aeronautical Research Committee Technical Report 1768 (1936).Google Scholar
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5. Winter, K.G., Comparative tests of thick and thin turning vanes in the Royal Aircraft Establishment 4 x 3ft wind tunnel; Reports and Memoranda No 2589; August 1947.Google Scholar
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