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In order to evaluate the behavior of the intermediate experimental vehicle (IXV) in the upper layer of the atmosphere, series of computations were carried out by means of the Direct Simulation Monte Carlo (DSMC) method, which are reported hereby. First an introduction is given about the IXV mission followed by a short explanation on DSMC and the computational methodology. A first validation case is demonstrated for computations based on the geometry of the Apollo capsule, showing good agreement with a reference in literature. Then, simulations of the IXV are presented, including flow-thruster interaction. Finally, the result matrix of aerodynamic properties is shown.

Evaluation of the aerodynamic properties of the intermediate experimental vehicle in the rarefied and transitional regime