The compressible laminar boundary layer with heat transfer and small pressure gradient

Abstract

A perturbation method for the calculation of velocity and temperature profiles and skin-friction and heat-transfer characteristics for two-dimensional, compressible lsminar boundary layers with heat transfer and a small arbitrary pressure gradient is presented.The permissible pressure gradients include those of a form and magnitude usually encountered over slender aerodynamic shapes in supersonic flight.The method applies for any constant Rmndtl number, but results, aside from special examples, are presented for a Prandtl nuniberof 0.72.For the case of heat transfer, the w&U temperature is assumed constant..&A large number of universal functions are given in tabular form, so that the amount of effort required in a practical.applicationis reduced to the arithmetic combination of several tabulated values.The u computation procedure is summarized in a section entitled "JWIZICA!ITON OF AN.KLYSIS."The combined effects of heat transfer and pressure gradient on boundary-kyer characteristics are demonstrated by applying the results of the analysis to two representative wings.