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Supersonic Flow Past Bodies of Revolution with Thin Wings of Small Aspect Ratio

Published online by Cambridge University Press:  07 June 2016

P. M. Stocker
P. M. Stocker*
Affiliation:
Department of Mathematics, The University, Manchester
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Summary

The method developed by G. N. Ward for the treatment of slender pointed bodies in a uniform supersonic stream is applied to three special cases.

  • (i) Supersonic flow past a body of revolution with thin wings of symmetrical section and of small aspect ratio at zero incidence.

  • (ii) Supersonic flow past a body of revolution with plane wings of small aspect ratio set at incidence to the body, the whole being at incidence to the stream.

  • (iii) Supersonic flow past a body of revolution with a plane fin of small aspect ratio set at incidence, the whole being at incidence to the stream.

The pressure distribution on the wing has been calculated for a special case of (i) and is given in the Appendix.

Type
Research Article
Information
Aeronautical Quarterly , Volume 3 , Issue 1 , May 1951 , pp. 61 - 79
Copyright
Copyright © Royal Aeronautical Society. 1951

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References

1. Ward, G. N. (1949). Supersonic Flow past Slender Pointed Bodies. Quarterly Journal of Mechanics and Applied Mathematics, 2 (1949), 75–97.CrossRefGoogle Scholar