Supersonic Aerodynamic Heating of a Yawed Sphere-Cone Wind-Tunnel Model

摘要

The steady-state pressure and heat-transfer distributions on a sphere-cone configuration with laminar boundary layer have been determined in a wind tunnel at yaw angles, 0 degree and 6 degrees, and at nominal Mach numbers, 3 and 5. Comparison of the 0 degree yaw local heat-transfer rates with those of the windward body streamline at 6 degrees yaw show a maximum increase for corresponding body stations of approximately 100 percent. The 0 degree yaw heat-transfer results show good agreement with the recent theory of Powers and Krahn.