T equations for the compressible two-dimensional laminar boundary layer, with heat transfer and arbitrary pressure gradient, originally set forth by Stewartson, have been solved by Cohen and Reshotkofor a number of pressure gradients and wall-to-f reestream stagnation temperature ratios. The purpose of this note is to compare some experimental data with the velocity profiles and displacement thicknesses computed from these solutions for an actual body, with nonsimilar pressure distribution and adiabatic wall. This experiment was conducted during a study of the effects of three-dimensional roughness on transition of the laminar boundary layer on a cooled blunt body. It was necessary during the course of the study to determine accurately the laminar boundary-layer profile and thickness over the body surface; however, a search of the literature failed to provide an experimental verification of the accuracy of using the Cohen and Reshotko solutions to calculate velocity profiles for the conditions of interest. Kemp et al. found that the laminar heat-transfer rates to blunt, highly cooled bodies could be predicted by assuming local similarity, but data for velocity profiles, and for conditions near adiabatic wall temperatures, are not available. The test body used was a hemisphere-cylinder with an isothermal wall temperature equal to the freestream stagnation temperature Tw = T0, in a flow of air having a freestream Mach number of 2.01. This case satisfies approximately the conditions set for the solutions given in Ref. 1: Prandtl number equal to one, linear viscosity-temperature relation across the boundary layer, and an isothermal surface. The solutions were applied in a point-by-point fashion along the surface of the body using the measured static pressure distribution. This pressure distribution, for the hemisphere-cylinder model used in the experiment, can be seen in Fig. 1. The measured Joressure distribution is compared with the Newtonian prediction,