Abstract
A comprehensive set of exact solutions to the first-order boundary-layer equations has been computed using the finite difference computer programme of Sells, with and without wall cooling. The effects of Prandtl number, wall cooling and Mach number on separation point location were studied. Values of displacement thickness, skin friction coefficient and Stanton number are displayed graphically for the supersonic flow over a circular concave arc, for a subsonic cooled cylinder and for the case of a linearly retarded velocity distribution. The influence of pressure gradient on recovery factor was studied. Velocity and temperature profiles are shown for four cold wall cases. The exact computer results show the errors in many of the more approximate methods available for the case whereUe=U∞(1 -X/L). The importance of second-order effects and the applicability of a first-order solution are discussed briefly.
Publisher
Cambridge University Press (CUP)
Subject
Mechanical Engineering,Mechanics of Materials,Condensed Matter Physics
Reference13 articles.
1. Stewartson, K. 1964 The Theory of Laminar Boundary Layers in Compressible Fluids .Oxford:Clarendon.
2. Morduchow, M. 1965 Review of theoretical investigations on effect of heat transfer on laminar separation AIAA J. 3,1377.
3. Monaghan, R. J. 1961 Effects of heat transfer on laminar boundary layer development under pressure gradients in compressible flow.Aero. Res. Counc. R. & M. no. 3218.
4. Luxton, R. E. & Young, A. D. 1962 Generalised methods for calculation of the laminar compressible boundary layer characteristics with heat transfer and non-uniform pressure distribution.Aero Res. Counc. R. & M. no. 3233.
5. Gadd, G. E. 1957 A review of theoretical work relevant to the problem of heat transfer effects on laminar separation ARC CP 331.
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