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Effect of Shock Boundary Layer Interaction on Aerofoil Pressure Distributions at Transonic Speeds

Published online by Cambridge University Press:  04 July 2016

D. Tirumalesa
D. Tirumalesa*
Affiliation:
National Aeronautical Laboratory, Bangalore
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Summary

A method of improving pressure distributions predicted by inviscid theory over two-dimensional aerofoils at transonic speeds taking into account shock-wave turbulent boundary layer interaction as obtained in the case of the flat plate is described.

The method was applied to a non-lifting circular arc aerofoil of eight per cent relative thickness. The shock wave location, pressure distribution and drag coefficient were calculated and compared with experimental and inviscid theoretical results.

It has been found that the method gives results which are consistent with experimental results in various aspects.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 67 , Issue 634 , October 1963 , pp. 674 - 677
Copyright
Copyright © Royal Aeronautical Society 1963

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References

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