Experimental measurements of the profile characteristics of the supersonic turbulent boundary layer in a region of zero pressure gradient and in a region of moderate adverse pressure gradient along the curved surface of an isentropic ramp model are reported. Detailed surveys of impact pressure, static pressure and total temperature were taken through the boundary layer and local values of wall shear stress were obtained using the Preston tube technique. The measurements were made in a supersonic wind tunnel for a nominal tunnel nozzle setting of Mach 3.5. The data are for an adiabatic wall with values of momentum thickness Reynolds number ranging from 19,000 to 42,000. The experiment is described in detail and the mean profile data are presented in tabular form. Fluctuation data obtained using constant temperature hot wire anemometry are presented for one station in the region of zero pressure gradient and for one station in the region of adverse pressure gradient. (Author).

The experimental data reported in Part 1 are analyzed. Turbulent boundary layer equations applicable to compressible flow over a surface with longitudinal curvature are evaluated by numerical integration using the tabulated profile data. Curvature corrections to the equation for conservation of streamwise momentum are shown to be small but of the same order of magnitude as the wall shear stress. The data are shown to correlate in law of the wall and velocity defect dimensionless coordinates using an integral compressibility transformation. Values of skin friction coefficient calculated using the experimental data are compared to other experimental data and to values predicted using the Spalding-Chi method. (Author).