Computational modeling and validation for hypersonic inlets
Abstract
Hypersonic inlet research activity at NASA is reviewed. The basis is the experimental tests performed with three inlets: the NASA Lewis Research Center Mach 5, the McDonnell Douglas Mach 12, and the NASA Langley Mach 18. Both three-dimensional parabolized Navier-Stokes and Navier-Stokes codes were used to compute the flow within the three inlets. Modeling assumptions in the codes involve the turbulence model, the nature of the boundary layer, shock wave boundary layer interaction, and the flow spilled to the outside of the inlet. Use of the codes in conjunction with the experimental data are helping to develop a clearer understanding of the inlet flow physics and to focus on the modeling improvements required in order to arrive at validated codes.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- January 1990
- Bibcode:
- 1990STIN...9022011P
- Keywords:
-
- Computational Fluid Dynamics;
- Hypersonic Inlets;
- Inlet Flow;
- Navier-Stokes Equation;
- Shock Wave Interaction;
- Turbulence Models;
- Boundary Layers;
- Computer Programs;
- Hypersonic Speed;
- Mathematical Models;
- Parabolic Differential Equations;
- Propulsion;
- Proving;
- Research Facilities;
- Fluid Mechanics and Heat Transfer