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An integral-transform method for shock–shock interaction studies

Published online by Cambridge University Press:  28 March 2006

N. L. Arora
N. L. Arora
Affiliation:
Department of Aeronautical Engineering, Technological University, Delft
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Abstract

An analytic solution is obtained for the head-on collision of strong shock waves with supersonically moving, axisymmetric, slender bodies. A new method of the solution is developed using integral transforms. Pressure distributions on the surface of a cone illustrate the effects of shock strength and body speed. The results are compared with those of Blankenship (1965), which were obtained by numerical methods.

It is also shown that the same analysis can, with certain modifications, be adapted for treating the shock-shock interaction on thin two-dimensional aerofoils of arbitrary shape at small incidence.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 34 , Issue 2 , 12 November 1968 , pp. 209 - 228
Copyright
© 1968 Cambridge University Press

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References

Blankenship, V. D. 1905 J. Fluid Mech. 22, 599.
Blankenship, V. D. & Merritt, D. L. 1966 AIAA J. 4, 2054.
Lighthill, M. J. 1949 Proc. Roy. Soc. A, 198, 454.
Ludloff, H. F. & Friedman, M. B. 1952 J. Aero. Sci. 19, 425.
Moore, F. K. 1953 NACA Rep. no. 1165.
Smyrl, J. L. 1963 J. Fluid Mech. 15, 223.
Sneddon, I. N. 1951 Fourier Transforms. New York: McGraw-Hill.
Ting, L. & Ludloff, H. F. 1952 J. Aero. Sci. 19, 317.