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Singularities of attached shock waves in steady axially symmetric flow

Published online by Cambridge University Press:  28 March 2006

Henri Cabannes  and
Claude Stael
Henri Cabannes
Affiliation:
Professeur à la Faculté des Sciences de Paris
Claude Stael
Affiliation:
Ingénieur des Arts et Manufactures
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Abstract

An I.B.M. 704 electronic computer was used to integrate the differential equations, which determine the shock singularity, when the velocity after the shock on a body is subsonic. The results are given in twenty-two cases corresponding to three different bodies; the procedure followed was outlined in a previous paper (Cabannes 1952).

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 10 , Issue 2 , March 1961 , pp. 289 - 296
Copyright
© 1961 Cambridge University Press

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References

Cabannes, H. 1951a Détermination de l'onde de choc attachée lorsque la vitesse aval à la pointe est subsonique. Publ. Scient. et Tech. du Ministère de l'Air, 250, 181–95.Google Scholar
Cabannes, H. 1951b Etude de l'onde de choc attachée dans les écoulements de révolution. I. Cas d'un obstacle terminé par une ogive. Rech. aéro. 24, 17–23.Google Scholar
Cabannes, H. 1952 Etude de l'onde de choc attachée dans les écoulements de révolution. II. Cas d'un obstacle terminé par un cône. Rech. aéro., 27, 7–16.Google Scholar
Kopal, Z. 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 symmetrical body placed in a uniform stream. N.A.C.A. Tech. Note 2505.