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The Prediction of Aerofoil Pressure Distributions for Sub-Critical Viscous Flows†

Published online by Cambridge University Press:  07 June 2016

R. C. Lock ,
P. G. Wilby  and
B. J. Powell
R. C. Lock
Affiliation:
Aerodynamics Division, National Physical Laboratory
P. G. Wilby
Affiliation:
Aerodynamics Division, National Physical Laboratory
B. J. Powell
Affiliation:
Aerodynamics Division, National Physical Laboratory
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Summary

The paper first describes an approximate method for calculating inviscid flows round arbitrary aerofoils at sub-critical Mach numbers, based on second-order theory with empirical improvements to give better agreement with exact theory; several comparisons are shown. This method is then used as the basis of an iterative procedure for calculating the effect of the boundary layer on the surface pressures and overall forces; several comparisons are given with recent experimental results.

Type
Research Article
Information
Aeronautical Quarterly , Volume 21 , Issue 3 , August 1970 , pp. 291 - 302
Copyright
Copyright © Royal Aeronautical Society. 1970

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Footnotes

†

This note is based on an abstract from a paper of the same title submitted for the AGARD Meeting on Transonic Aerodynamics held in Paris in September 1968, and issued in AGARD Conference Proceedings 35.

References

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