@techreport{oai:jaxa.repo.nii.ac.jp:00043377,
 author = {山本, 行光 and 秋元, 敏男 and 鈴木, 尚行 and Yamamoto, Yukimitsu and Akimoto, Toshio and Suzuki, Naoyuki},
 month = {Nov},
 note = {An unmanned winged vehicle for space transportation called H-II Orbiting Plane (HOPE) has been studied by National Space Development Agency of JAPAN (NASADA). The gross weight is planned about 9.O tons at launch with the payload of about 1.2 tons. The current baseline configuration of the HOPE has a double delta wing with tip fins. The double delta type wing planform is expected to have smaller longitudinal trim change over all the flight regions and tip fins are adopted in order to gain easier access to Space Station or other platforms than the vertical tail wings on the fuselage. 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 lateral and directional aerodynamic characteristics. This work has been done as the joint research of National Aerospace Laboratory (NAL) and NASDA. Numerical computations were carried out at M infinity =7.0 and Reynolds number of 2.5 by 106 at angles of attack 0, 20 and 40 degrees with yaw angle of 5 deg. Numerical results were compared with experimental data obtained from hypersonic wind tunnel (HWT) at NAL., 資料番号: NALSP0010048, レポート番号: NAL SP-10},
 title = {HOPEまわりの極超音流数値シミュレーション},
 year = {1989}
}