New Similarity Solutions for Hypersonic Boundary Layers with Applications to Inlet Flows

摘要

A re-examination of self-similar solution possibilities for steady laminar boundary layers is given for nonadiabatic strongly hypersonic flows of an ideal gas. Two apparently new solutions are found, pertaining to adverse pressure gradients, both of which involve no separation with distance into the pressure rise. The first involves an exponential pressure rise on a cooled similarly shaped body, whereas the second involves a modified ramp type pressure rise. The skin friction, heat transfer, displacement thickness, and weak viscous interaction-induced pressure change properties of these two solution families are analyzed in detail, including their application to high-speed inlet type of flows.