Linear Stability of Hypersonic Boundary Layers on the Basis of an Euler-/Boundary-Layer Method

Abstract

In order to successfully design future hypersonic space vehicles prediction and control of transition are most important topics. In this contest applicable engineering tools are required. The idea here is to use an Euler-/boundary-layer approach 2nd-order boundary-layer theory for computing laminar mean flow and local linear stability theory for estimating transition location. Advantages of the aforementioned mean flow computation are the following:Firstly, Euler-/boundary- layer methods have the advantage of less CPU-time requirements compared to Navier-Stokes methods. Secondly, the principle problem of computing a laminar steady-state mean flow solution at Reynolds numbers where unsteady modes do physically exist is circumvented.