4015 Numerical Simulation of Unsteady Flowfield around Vertical Landing Rocket Vehicle with Jet Ejection

Abstract

Computations of unsteady flowfield around the rocket vehicle is performed by using Large Eddy Simulations. The method is applied to the flight environment of Reusable Vehicle Testing with jet ejection. The interaction between freestream and the opposing jet from the vehicle is calculated by varying the angle of attack. Temporal variations of surface pressure acting on the vehicle are obtained. It is found from the calculated results that the frequency of pressure fluctuation for the RVT flight environment becomes shorter than that for the wind tunnel condition by a factor of 10 due to the scale effect.