Model for highspeed interaction heating
Abstract
A boundarylayer model with application to highspeed flow separation in compression corner geometries is described. Integration through regions of separating/reattaching flow is facilitated through the use of an inverse boundary layer procedure that computes the pressure gradient for a given boundarylayer displacement thickness and displacement mass flow. Comparisons with NavierStokes calculations for a confined separated flow, using the ReyhnerFluggeLotz approximation in the reverse flow region, are good and have served to validate the boundarylayer approach. The viscousinviscid interaction occurring in these flows are accounted for with the physicallysound coupling scheme developed recently by Wigton and Holt. A specific algorithm for hypersonic shock wave boundarylayer interactions is developed using the Newtonian flow approximation. Future calculations appropriate to laminar and turbulent compression corner experimental data are outlined.
 Publication:

Planetary Science Inst. Report
 Pub Date:
 December 1982
 Bibcode:
 1982psi..rept.....L
 Keywords:

 Aerodynamic Heating;
 Hypersonic Boundary Layer;
 Hypersonic Flow;
 Separated Flow;
 Shock Wave Interaction;
 Turbulent Boundary Layer;
 Boundary Layer Equations;
 Computational Fluid Dynamics;
 Displacement;
 NavierStokes Equation;
 Pressure Gradients;
 Shock Wave Interaction;
 Fluid Mechanics and Heat Transfer