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On the Corner Boundary Layer with Favourable Pressure Gradient

Published online by Cambridge University Press:  07 June 2016

M Zamir
M Zamir*
Affiliation:
Department of Applied Mathematics, University of Western Ontario
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Summary

Solutions of equations governing the flow in the plane of symmetry of a corner boundary layer with favourable pressure gradients are presented. The results indicate that as the pressure gradient is reduced the secondary flow in the plane of symmetry reverses its direction from a flow into the corner to an outflow away from the corner, the main velocity profile being of the separation type with zero gradient at the wall and a point of inflection within the boundary layer. As the pressure gradient is reduced further the numerical method of solution is found to break down, possibly because of a drastic change of character in the family of solutions. This may be indicative of a corresponding change of character in the physical flow which, it is hoped, may clarify some of the unexplained phenomena disclosed by recent experiments on the corner boundary layer with zero pressure gradient.

Type
Research Article
Information
Aeronautical Quarterly , Volume 23 , Issue 2 , May 1972 , pp. 161 - 168
Copyright
Copyright © Royal Aeronautical Society. 1972

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References

1. Zamir, M Boundary layer flow in a streamwise corner. PhD thesis, University of London, 1968.Google Scholar
2. Zamir, M Boundary layer theory and the flow in a streamwise corner. The Aeronautical Journal, Vol 74, p 330, April 1970.Google Scholar
3. Zamir, M Young, A D Experimental investigation of the boundary layer in a streamwise corner. Aeronautical Quarterly, Vol XXI, p 313, November 1970.Google Scholar
4. Zamir, M Young, A D Similar and asymptotic solutions of the incompressible laminar boundary layer equations with suction. Aeronautical Quarterly, Vol XVIII, p 103, May 1967.Google Scholar
5. Schlichting, H Boundary Layer Theory. McGraw-Hill, 1968.Google Scholar