@article{oai:jaxa.repo.nii.ac.jp:00021784,
 author = {上野, 篤史 and 牧野, 好和 and 高谷, 亮太 and 佐藤, 一成 and 磯, 英雄 and 三友, 俊輝 and Ueno, Atsushi and Makino, Yoshikazu and Takaya, Ryota and Satou, Kazushige and Iso, Hideo and Mitomo, Toshiteru},
 issue = {6},
 journal = {日本航空宇宙学会論文集, Journal of the Japan Society for Aeronautical and Space Sciences},
 month = {Dec},
 note = {This paper describes a method of spillage drag measurement with aid of CFD at supersonic speeds. In a wind tunnel testing, the number of pressure data points is limited and is not enough to capture pressure distribution needed for an accurate calculation of spillage drag. In this method, a wind tunnel testing provides pressure data at twenty points, by which a CFD analysis is validated. Then, the pressure data obtained by the wind tunnel testing is corrected based on pressure distribution obtained by the CFD analysis. The spillage drag is calculated using corrected data. When the intake is at the supercritical condition, the spillage drag does not exist. The present method correctly shows the spillage drag of nearly zero at the supercritical condition, while the spillage drag calculated only by wind tunnel data is negative. In addition, the spillage drag obtained by the present method is increased as the intake mass flow ratio is decreased, which agrees with the general trend. These results support the effectiveness of the present method., 形態: 図版あり, Physical characteristics: Original contains illustrations, 資料番号: DS1740338003},
 pages = {235(17)--242(24)},
 title = {CFDを援用した小型超音速旅客機のスピレージ抵抗計測},
 volume = {65},
 year = {2017}
}