@techreport{oai:jaxa.repo.nii.ac.jp:00002127,
 author = {田口, 秀之 and 藤田, 和央 and 進藤, 重美 and 津田, 尚一 and 平林, 則明 and 小山, 忠勇 and 伊藤, 良三 and Taguchi, Hideyuki and Fujita, Kazuhisa and Shindo, Shigemi and Tsuda, Shoichi and Hirabayashi, Noriaki and Koyama, Tadao and Ito, Ryozo},
 month = {Feb},
 note = {極超音速実験機のマッハ5空力特性を0.5mJAXA極超音速風洞で取得した。機体模型の6分力計測を行うとともに、実験機の飛行環境を摸擬したCFD(Computational Fluid Dynamics)解析を実施した。結果として、迎角に対する空力係数の変化は風洞試験とCFDで概ね一致した。風洞試験においては、機体上面に大規模な剥離域が観察された。風洞試験とCFDにおける空力係数の違いは、剥離域の違いの影響と推測された。エンジンを装着した形状では、法線力係数と軸力係数が上昇した。, Mach 5 aerodynamic coefficients for a hypersonic experimental airplane are examined at JAXA 0.5 m hypersonic wind tunnel. Six DOF (Degree Of Freedom) forces for the model are measured and evaluated. CFD (Computational Fluid Dynamics) analyses for the same airframe are performed simulating real flight condition for the experimental airplane. As a result, variations of aerodynamic coefficients on angle of attack for both wind tunnel test and CFD analysis are consistent in general. Large separation region is observed on the upper surface of the body at the wind tunnel test. It is presumed that the difference of aerodynamic coefficients has occurred by the difference in flow separation between the wind tunnel test and CFD. Lateral force coefficient and axial force coefficient are raised with engine installed configuration., 資料番号: AA0063912000, レポート番号: JAXA-RR-07-047},
 title = {極超音速機のマッハ5空力特性試験},
 year = {2008}
}