A simplified method has been developed for the calculation of heat transfer and skin friction in the compressible laminar boundary layer with an arbitrary Prandtl number near unity and an arbitrary streamwise pressure gradient and wall temperature distribution. By comparison of numerical results with some exact solutions, the method is shown to give accurate results with some exact solutions, the method is shown to give accurate results for the case of boundary-layer cooling when a certain fifth-dgree polynomial is used for the thermal profile. The use of this polynomial also results in recovery factors which are accurate to within a few percent on both the flat plate and the circular cylinder normal to flow.

A theoretical study is made of the effect of pressure gradient, wall temperature, and Mach number on laminar boundary-layer characteristics and, in particular, on the skin-friction and heat-transfer coefficients, on the separation point in an adverse pressure gradient, on the wall temperature required for complete stabilization of the laminar boundary layer, and on the minimum critical Reynolds number for laminar stability. The Prandtl number is assumed to be unity and the coefficient of viscosity is assumed to be proportional to the temperature, with a factor arising from the Sutherland relation. A simple and accurate method of locating the separation point in a compressible flow with heat transfer is developed. Numerical examples to illustrate the results in detail are given throughout.

Thorough introduction to boundary layer problems offers an ordered, logical presentation accessible to undergraduates. The text's careful expositions of the limitations and accuracy of various methods will also benefit professionals. 1962 edition.