Model for high-speed interaction heating
Abstract
A boundary-layer model with application to high-speed 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 boundary-layer displacement thickness and displacement mass flow. Comparisons with Navier-Stokes calculations for a confined separated flow, using the Reyhner-Flugge-Lotz approximation in the reverse flow region, are good and have served to validate the boundary-layer approach. The viscous-inviscid interaction occurring in these flows are accounted for with the physically-sound coupling scheme developed recently by Wigton and Holt. A specific algorithm for hypersonic shock wave boundary-layer 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;
- Navier-Stokes Equation;
- Pressure Gradients;
- Shock Wave Interaction;
- Fluid Mechanics and Heat Transfer