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Three-dimensional laminar compressible boundary layers with large injection

Published online by Cambridge University Press:  29 March 2006

C. S. Vimala  and
G. Nath
C. S. Vimala
Affiliation:
Department of Applied Mathematics, Indian Institute of Science, Bangalore 560012 Present address: Aerodynamics Division, National Aeronautical Laboratory, Bangalore.
G. Nath
Affiliation:
Department of Applied Mathematics, Indian Institute of Science, Bangalore 560012
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Abstract

The effect of large mass injection on the following three-dimensional laminar compressible boundary-layer flows is investigated by employing the method of matched asymptotic expansions: (i) swirling flow in a laminar compressible boundary layer over an axisymmetric surface with variable cross-section and (ii) laminar compressible boundary-layer flow over a yawed infinite wing in a hypersonic flow. The resulting equations are solved numerically by combining the finite-difference technique with quasi-linearization. An increase in the swirl parameter, the yaw angle or the wall temperature is found to be capable of bringing the viscous layer nearer the surface and reducing the effects of massive blowing.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 71 , Issue 4 , 28 October 1975 , pp. 711 - 727
Copyright
© 1975 Cambridge University Press

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