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Curvature of attached shock waves in steady axially symmetric flow

Published online by Cambridge University Press:  28 March 2006

E. Bianco ,
H. Cabannes  and
J. Kuntzmann
E. Bianco
Affiliation:
Faculties of Sciences of Grenoble and Marseille(France)
H. Cabannes
Affiliation:
Faculties of Sciences of Grenoble and Marseille(France)
J. Kuntzmann
Affiliation:
Faculties of Sciences of Grenoble and Marseille(France)
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Abstract

An electronic computer has been employed to calculate the ratio between the initial radii of curvature of the attached shock wave and the body for an axially symmetrical body in a uniform supersonic stream. The results are obtained with 4 exact digits for more than 200 cases. They extend results obtained previously (Cabannes 1951) by means of numerical integration.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 7 , Issue 4 , April 1960 , pp. 610 - 616
Copyright
© 1960 Cambridge University Press

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References

Cabannes, H. 1951 Etude de l'onde de choc attachée dans les écoulements de révolution. Rech. aéro., 24, 17–23.Google Scholar
Kopal, Zdenek 1947 Tables of supersonic flow around cones. Massachusetts Institute of Technology.
Shen, S. F. & Lin, C. C. 1951 On the attached curved shock in front of a sharp-nosed axially symmetrical body placed in a uniform stream. N.A.C.A. Technical Note, 2505.Google Scholar
Rao, P. S. 1956 Supersonic bangs. Aeronaut. Quart., 7, 135–55.Google Scholar