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Note on the Application of Busemann's Formula to a Simple Two-Dimensional Curved Aerofoil Section

Published online by Cambridge University Press:  28 July 2016

J. A. Dunsby
J. A. Dunsby*
Affiliation:
Technical Department, Royal Aeronautical Society
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Extract

The theoretical aerodynamic properties of supersonic aerofoils of polygonal section are well known. This note describes the results obtained by applying supersonic aerofoil theory to a simple curved aerofoil of arbitrary maximum thickness position, the leading and trailing edges of which are pointed.

The results for a symmetrical curved section are compared with the theoretical properties of a symmetrical double-wedge section.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 57 , Issue 513 , September 1953 , pp. 600 - 603
Copyright
Copyright © Royal Aeronautical Society 1953

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References

1. Lock, C. N. H. (1944). Examples of the Application of Busemann's Formula to Evaluate the Aerodynamic Force Coefficients on Supersonic Aerofoils. R. & M. 2101, 1944.Google Scholar