CFD Analysis of a Launch Vehicle with Reverse Flow Nozzles-A Validation Study

摘要

CFD analysis has been carried out over a typical wind tunnel model Launch Abort System (LAS) Configuration. The viscous turbulent flow studies have been carried out to generate aerodynamic coefficients at Mach 1.6, various angles of attack under jet-on and jet-off conditions using the PARAS-3D code. The present CFD solver is validated using the aerodynamic coefficient of LAS data obtained through CFD and Wind Tunnel experiments. The comparison shows good match with experimental data at lower angles of attack and reasonable match at higher angles of attack under jet-off and jet-on conditions. This study shows that CFD can be applied to predict the aerodynamic coefficients and flow field analysis of launch vehicle with reverse flow jets.