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Experiments in Fluids
Published in: Experiments in Fluids 4/2003

01-10-2003 | Original Paper

Experimental determination of the free-stream disturbance field in a short-duration supersonic wind tunnel

Authors: J. Weiss, H. Knauss, S. Wagner

Published in: Experiments in Fluids | Issue 4/2003

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Abstract

The free-stream disturbance field in a short-duration supersonic wind tunnel is investigated at a nominal Mach number of Ma=2.54. A specially designed constant-temperature anemometer is used to be able to draw a complete fluctuation diagram within one wind tunnel run (testing time: 120 ms). It is shown that the disturbance field is dominated by acoustic waves radiated from the turbulent boundary layer on the nozzle and the sidewalls, like in conventional supersonic wind tunnels. The acoustic field appears to be composed of highly localized shivering Mach waves superimposed on a background of eddy Mach waves.
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Footnotes
1
A similar approach was recently followed by Comte-Bellot and Sarma (2001) with a constant voltage anemometer (CVA) in a supersonic boundary layer.
 
2
This is equivalent to assuming that G depends only on τ, which is sufficient for the present purpose.
 
3
This value is close to the average pressure fluctuation at x/l=0.76: (<p>)0.76=(<p>EMW)0.76=0.130%.
 
4
The boundary layer thickness was computed with the code of Harris and Blanchard (1982) assuming laminar–turbulent transition at the nozzle throat. The computational results agree very well with measurements at the nozzle output.
 
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Metadata
Title
Experimental determination of the free-stream disturbance field in a short-duration supersonic wind tunnel
Authors
J. Weiss
H. Knauss
S. Wagner
Publication date
01-10-2003
Publisher
Springer-Verlag
Published in
Experiments in Fluids / Issue 4/2003
Print ISSN: 0723-4864
Electronic ISSN: 1432-1114
DOI
https://doi.org/10.1007/s00348-003-0623-z

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