An unmanned winged vehicle for space transportation called H-II Orbiting Plane (HOPE) is studied by National Space Development Agency of Japan (NASDA). Hypersonic CFD analyses were performed for HOPE 63 model proposed by NASDA. The effects of Reynolds number, Mach number, angles of attack, and yaw angles are investigated in detail. In order to use CFD for more practical designing purposes, analyses of control surfaces and gas jets are also made. In addition, calculations of chemically nonequilibrium hypersonic flow are conducted for OREX (Orbiter Re-entry Experiment) model. The purposes of the present study are: (1) to demonstrate the validity of the numerical code for aerothermodynamic heating, (2) to investigate the applicability of CFD for control problems, and (3) to develop reliable gas CFD code. Numerical simulations were performed using flux-split upwind Navier-Stokes code.


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