Hypersonic Flow Analysis of Re-entry Vehicles Using Three Dimensional Navier-Stokes Equations

摘要

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. The analytical method is used to calculate the Jacobian matrix. Flow parameters and convective heat transfer are analyzed on Apollo AS-202 Command Module. Also, algebraic Baldwin-Lomax turbulence model and 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.