Skin Friction Measurements at a Mach Number of Three and Momentum Thickness Reynolds Numbers Up to a Half Million

摘要

Surface shear stress measurements were made in the Flight Dynamics Laboratory's M=3 High Reynolds Number wind tunnel. The primary purpose of this research was to make shear stress measurements at very high Reynolds numbers for near adiabatic wall and zero pressure gradient conditions. The results are presented as the local skin friction coefficient versus both the momentum thickness and the length Reynolds number. The investigation was conducted on the nozzle wall at a nominal Mach number of three over the Reynolds number range of 20,000 < or = R sub e sub theta < or = 500,000. The surface shear stress was measured with a balance. The resulting skin friction coefficients were verified by simultaneous measurements made with a Preston tube. The skin friction coefficient was also calculated using the Von Karman integral method. They were then compared with the experimental results of Matting et al., and Moore-Harkness along with the theories of Van Driest, Spalding-Chi, Wilson, and Shang et al.