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Pressure fluctuations caused by transonicshock/boundary-layer interaction

Published online by Cambridge University Press:  04 July 2016

A. R. G. Mundell and
D. G. Mabey
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Summary

An analysis of an extensive series of unsteady and steady pressure measurements at transonic speeds on a rigid 12% thick NACA 16 series aerofoil reveals a useful classification of the type of excitation characteristics of particular flow regions.

The pressure fluctuation measurements suggest that when the shock from the aerofoil reaches the tunnel roof, serious interference (both dynamic and static) occurs.

The RAE 2 ft × 1½ ft Transonic Tunnel used for the tests has low levels of flow unsteadiness at low frequencies, making it a useful facility for basic research in time-dependent aerodynamics.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 90 , Issue 897 , September 1986, pp. 274 - 282
Copyright
Copyright © Royal Aeronautical Society 1986 

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Footnotes

*

Aerodynamics Department, Royal Aircraft Establishment, Farnborough.

†

Aerodynamics Department, Royal Aircraft Establishment, Bedford.

References

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