Aerodynamic Heat Prediction on a 15 degree Cone-Cylinder-Flare Configuration Using 2D Axisymmetric Viscous Transient CFD

Abstract

This paper investigates a method to predict aerodynamic heating on a supersonic flare body using a 2D axisymmetric transient viscous CFD simulation. Five turbulent models and three simulation time step sizes were utilized. The surface temperature of the rocket predicted by the simulations was compared to the published experimental data obtained from the first 26 s of a rocket flight test. It was found that the Transition SST model performed better than the others. Furthermore, the simulation results matched the experimental data well during the first 7 second. Then the difference between the simulation results and the experimental data became noticeable. But their trends were still the same and CFD simulation overestimated the temperature most of the time