AN EFFICIENT 3D NAVIER-STOKES ANALYSIS FOR EVALUATION OF HYPERSONIC VEHICLES

THE NEED EXISTS FOR A COST EFFECTIVE 3D FLOW ANALYSIS CODE THAT WILL ACCURATELY MODEL THE VISCOUS FLOW FIELDS FOR HYPERSONIC VEHICLES INCLUDING FLOW FEATURES THAT ARE ACTIVATED FOR THERMAL PROTECTION AND AEROCONTROL. THE PROPOSED EFFORT WILL RESULT IN A 3D NAVIER-STOKES CODE THAT IS OPTIMIZED FOR USE AS A DESIGN TOOL. THE CODE WILL ACCURATELY MODEL SHOCKS, BOUNDARY LAYERS, BLUNT BODY FLOWS, COOLING BY TRANSPIRATION AND SLOT INJECTION, SIDE-THRUSTING JETS, BASE FLOWS, AND REAL GAS EFFECTS. THE PHASE I OBJECTIVES ARE THE DEVELOPMENT OF THE BASIC CODE AND THE OPTIMIZING OF THE NUMERICAL ALGORITHM FOR HYPERSONIC FLOW FIELDS. THE APPROACH IS BASED ON MODIFING AN EXISTING 3D IMPLICIT FLUX-SPLIT NAVIER-STOKES CODE. THE NUMERICAL ALGORITHM WILL BE OPTIMIZED BY TAKING ADVANTAGE OF THE FACT THAT LARGE REGIONS OF THE FLOW FIELD WILL BE PREDOMINANTLY SUPERSONIC. A MULTIPLE ZONE CAPABILITY WILL BE ADDED TO ALLOW GEOMETRICALLY DISTINCT REGIONS WITH INDEPENDENT MESHESTO BE NUMERICALLY COUPLED ALONG COMMON BOUNDARIES. THE PHASE I CODE WILL BE DEMONSTRATED FOR A CASE HAVING SLOT INJECTION COOLING WITH A HYPERSONIC FREESTREAM.