ANALYSIS OF THREE DIMENSIONAL HYPERSONIC FLOW AROUND RE-ENTRY VEHICLE USING NAVIER-STOKES EQUATIONS
The purpose of this study is to develop an accurate and efficient CFD code that can be used in hypersonic flows. The flow analysis is based on the three dimensional Navier-Stokes equations. These equations are solved by using Newton’s method and the analytical method is used to calculate the Jacobian matrix. Flow parameters and convective heat transfer are analyzed on Apollo AS-202 Space Capsule. Also, one-equation Spalart-Allmaras turbulence model is used to analyze hypersonic turbulent flow since this turbulence model is numerically robust and generally gives good predictions in hypersonic applications.
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