摘要: Direct skin friction measurements were conducted in Texas A&M University's ACE Facility on a 2.75° half-angle wedge at Mach 6. The goal of the test program was to demonstrate the ability of different wall shear sensor technologies... 展开 Direct skin friction measurements were conducted in Texas A&M University's ACE Facility on a 2.75° half-angle wedge at Mach 6. The goal of the test program was to demonstrate the ability of different wall shear sensor technologies to detect transition and provide accurate measurements in different boundary layer states. The facility's total pressure was increased during the runs to obtain Reynolds numbers between 2×10~6 and 8×10~6 per meter. Without any trip, the boundary layer remained laminar. Different trip configurations were tested to force boundary layer transition near the center of the Reynolds number range. Surface temperature measurements were used to compute heat flux so that the Reynolds analogy could be used to compare with the directly measured turbulent skin friction, and static pressure measurements were used to detect transition and corroborate the direct skin friction sensors' identification of boundary layer transition. 收起