Abstract
The stability of supersonic boundary layer flow past a flat plate with compression ramp is investigated numerically to clarify the behavior of Tollmien-Schlichting waves. At a Mach number of 2.2, the two-dimensional periodic disturbances are introduced into the flow as the upstream boundary conditions and the boundary layer responses are studied through directly solving the 2D Navier-Stokes equations using a TVD scheme. Results are presented for a range of corner angles, including separated cases, and are compared with the asymptotic triple-deck theory. As for the development of Tollmien-Schlichting waves along the ramp, the wave growth is highly intensified as the ramp angle increases, and we find that this growth is governed by the increase in ρ ρ(∂u/∂y) at the so-called generalized inflection point.
