@techreport{oai:jaxa.repo.nii.ac.jp:00043345,
 author = {佐藤, 哲也 and 梶, 昭次郎 and Sato, Tetsuya and Kaji, Shojiro},
 month = {Nov},
 note = {In the airframe-integrated scramjet engines, the inlet flow is accompanied by a strong gradient of Mach number as well as mass flux owing to the forebody thick boundary layer which cannot be diverted outside engines because of its high temperature. If such engines are designed for uniform inlet flows they cannot endure this type of inlet flow gradient, and a strong pressure loss occurs at the inlet. In this study the flow mechanics of scramjet engines subject to a forebody boundary layer are investigated, and various phenomena such as compound choking and the transition of inlets from start to unstart conditions are revealed. First, the influence of boundary layers is studied by a combined one-dimensional stream tube model. Then the flow field of an engine is analyzed using a quasi-three-dimensional finite difference model. The explicit MacCormack method is used. It is shown that a scramjet engine designed for a uniform inlet flow experiences choking by the presence of a low-speed region like a boundary layer. This phenomenon is called compound choking. When a compound choking occurs, it is shown that the throat Mach number is not unity but that in the boundary layer the flow is subsonic while it is supersonic in the main strream region. The processes of transition of an inlet from start to unstart conditions are shown to depend remarkably on width and shear strength of the boundary layer. It is also shown that an engine with a sweep angle is very tolerant of such flow non-uniformities., 資料番号: NALSP0010016, レポート番号: NAL SP-10},
 title = {スクラムジェットエンジン内部流れの解析},
 year = {1989}
}