An unmanned winged vehicle for space transportation called H-II Orbiting Plane (HOPE)is being studied by the National Space Development Agency of JAPAN (NASDA). In the present paper, hypersonic computational fluid dynamics (CFD) analyses have been performed for the 62A, 62B, and 62C HOPE configurations in order to investigate aerodynamic and aerothermodynamic characteristics. This research has been carried out jointly by the National Aerospace Laboratory (NAL) and NASDA. Numerical computations were carried out at M∞=7.0 and Reynolds number of 2.5×10(exp 6) at angles of attack from 0, to 40 degrees with and without yaw angles. Numerical results were compared with experimental data obtained from the hypersonic wind tunnnel(HWT) at NAL.
HOPEの極超音速空力数値シミュレーション
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