A Model for the Analysis of Viscous Inviscid Interaction Effects on Blunt Bodies in Hypersonic Flight

摘要

A model for the study of viscous inviscid interactions is presented. The boundary layer equations are solved by means of an implicit finite difference scheme; the supersonic portion of the flow is calculated by characteristics including viscous terms, and the two sections of the flow matched. The possibility of a non-zero normal pressure gradient in the boundary layer is taken into account by the analysis. A shock point calculation which includes the effects of viscosity behind the shock is presented. The method is applied to a two-dimensional blunt body in hypersonic flight, and the significance of the model for high curvature and low Reynolds number conditions is discussed. A listing of the computer program which generated these results is included in the report. (Author)