Method for calculation of compressible laminar boundary layer with axial pressure gradient and heat transfer

Paul A. Libby, Morris Morduchow
naca-tn-3157
Jan 1954


A rapid and sufficiently accurate method, for most practical purposes, of determining laminar-boundary-layer characteristics in flow with a given free-stream Mach number and given velocity distribution at the edge of the boundary layer is presented. The method can be easily applied to flow with zero pressure gradient for any (constant) Prandtl number of the order of unity and any given temperature distribution along the wall.

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