Curved Test Section for Research on Transonic Shock Wave-Boundary Layer Interaction

摘要

A nozzle with a curved test section for a blowdown wind tunnel was designed to generate a transonic flow to investigate shock wave-boundary layer interaction on a convex curved wall at the lower side of the test section. The Mach number at the lower wall just in front of the shock wave may be varied between 1.2 and 1.45. The Mach number at the concave upper wall is or = 0.85. Measurements show the usefulness of the application of a simple one-dimensional analysis to determine the cross-sectional area distribution of the nozzle, the Mach number, and pressure distribution in front of the shock wave, and the dimensions of the downstream choke area.