An Integral Method for Two-Dimensional, Compressible, Adiabatic, Turbulent Boundary Layers

Abstract

An integral method is proposed to calculate adiabatic, turbulent boundary layers in compressible flow. For the description of the velocity profiles the Coles formulation is applied. The compressible effects are taken into account by the Stewartson-Illingworth transformation. Turbulence is modeled via the use of the entrainment concept. In order to cope with history effects of the boundary layer the lag-entrainment idea is adopted. The quality of the results of the integral method is documented for three different flow cases. The first tow cases are experiments in a low speed - and in a high supersonic flow, respectively. The third case uses Navier-Stokes results for an airfoil in subsonic, compressible flow for comparison.