@techreport{oai:jaxa.repo.nii.ac.jp:00002174,
 author = {苅田, 丈士 and 加藤, 周徳 and 小寺, 正敏 and 工藤, 賢司 and 村上, 淳郎 and 泉川, 宗男 and 渡辺, 修一 and Kanda, Takeshi and Kato, Kanenori and Kodera, Masatoshi and Kudo, Kenji and Murakami, Atsuo and Izumikawa, Muneo and Watanabe, Shuichi},
 month = {Dec},
 note = {極超音速気流中において機体形状がエンジンに流入する気流に及ぼす影響について実験により検討を行なった。3種類のスペースプレーンの機体模型を、1.27mマッハ10風洞と0.1mマッハ6.7風洞で実験した。3種の機体模型の前縁幅を点状、機体の半分、そして機体と同じ幅とした。ピトー圧をエンジン入口位置で測定した。機体前縁幅が最大の模型で、エンジンに流入する気流の一様性は最大となった。エンジンに流入する気流流量も、機体前縁幅が最大の模型で最大となった。この流量特性はエンジン高さが高いほど顕著となった。揚力抗力比は機体前縁幅が長い模型で大きくなること、層流境界層と衝撃波との干渉の影響は流れを横断する方向へは広がらないことも明らかとなった。, The effect of the airframe configuration on the condition of the airflow to an engine was investigated experimentally in a hypersonic flow. Three kinds of forebody models of an aerospace plane were tested in the 1.27-m Mach 9.7 wind tunnel and in the 0.1-m Mach 6.7 pilot-wind tunnel. The leading edge of each model had a different width, that is, a pointed configuration, half of the body width, and the same width as the body. Pitot pressure was measured at the location of the engine entrance. The uniformity of the airflow to an engine was greatest in the model with the longest width at its leading edge. The airflow rate to the engine was large with large width of the leading edge of the airframe. This feature became significant in an engine with large height at the entrance. It was also made clear that the ratio of lift to drag was large in the model with a long leading edge, and that the influence of the shock wave-laminar boundary layer interaction did not spread laterally., 資料番号: AA0063730000, レポート番号: JAXA-RR-07-007E},
 title = {Effect of airframe configuration on condition of airflow to engine in hypersonic flow},
 year = {2007}
}