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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*
Affiliation:
Technical Department, Royal Aeronautical Society

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
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