E ect of Concave Wall Geometry on Heat Transfer in Hypersonic Boundary Layers

Heat transfer measurements are made to investigate the e ects of concave surface curvature on a high-stagnation enthalpy boundary layer in a Mach 5.1 ow. Experiments are carried out using two curved models with 16 and 25 degree turning angles, and baseline planar models ( at plate and linear ramp) for comparative study. Streamwise and spanwise cross-sections are obtained. Signi cant destabilization of the boundary layer is observed over the adverse pressure gradient geometries. For the curved surfaces, the heat ux distribution appears to exhibit a quadratic dependence with streamwise distance, in contrast with the linear dependence observed on the linear ramp.