@inproceedings{oai:jaxa.repo.nii.ac.jp:00017346,
 author = {麻生, 茂 and 河野, 慎吾 and 井上, 慶 and Aso, Shigeru and Kawano, Shingo and Inoue, Kei},
 book = {宇宙輸送シンポジウム　平成14年度, Proceedings of Space Transportation Symposium FY2002},
 month = {Apr},
 note = {For the development of space planes the development of air breathing engines are in progress. One of the promising propulsion systems is SCRAM jet engine. In the present study two-dimensional and three-dimensional supersonic mixing flow fields have been investigated for the practical applications. The supersonic flow fields with fully developed turbulent boundary layer are established on the flat plate mode and secondary fuel flow (helium) is injected through flat plate model through two-dimensional oblique slot or three-dimensional oblique circular nozzle. The fuel injection angle of the secondary flow to the main flow is varied and the effects of the fuel injection angle of the flow field have been investigated. The testing conditions are free stream Mach number of M = 3.76, total pressure of 1.12 MPa, total pressure ratio of secondary gas to the free stream of 0.17 for slot on slot injection and 0.35 for circular injection respectively and fuel injection angle of 30, 90 and 150 deg measured from downstream. Air and helium are used for primary and secondary gases respectively., 資料番号: AA0045426010},
 pages = {37--42},
 title = {2次元および3次元超音速混合における噴射角の与える影響},
 year = {2003}
}