@inproceedings{oai:jaxa.repo.nii.ac.jp:00004729,
 author = {佐藤, 茂 and 宗像, 利彦 and 石河, 深雪 and Sato, Shigeru and Munakata, Toshihiko and Ishikawa, Miyuki},
 book = {宇宙航空研究開発機構特別資料: 第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 論文集, JAXA Special Publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010},
 month = {Feb},
 note = {第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 (2010年6月24日-25日. 米子コンベンションセンター BiG SHiP), 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25,  2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan, Japan Aerospace Exploration Agency has been investigating scramjet engines in Kakuda Space Center using RamJet Engine Test Facility (RJTF) et al. The engine performance tested at the flight condition of Mach 6 in RJTF showed very important characteristics depending on internal geometry. Above all only the strut height difference causes the difference of transition from weak combustion to intensive combustion. The transition is influenced by the shock waves generated in the engine, so that to capture the factor inducing the intensive combustion can make it possible to establish a concept for engine designing. Therefore authors have been analyzing a lot of data taken in RJTF with the help of CFD and checking phenomena caused by the shock waves in the engine. In the process it is found that the "hot area hot triangle" produced by both cowl shock wave and the strut shock wave can bring the desirable transition. In addition to the above, a theory has been reported that an incident shock wave to the downstream of a fuel injector can contribute flame holding in a scramjet engine. In this paper a consideration is described on the effect of relation of fuel injection and incident shock wave on the engine performance. The authors found the corresponding relation in the engine and propose a hypothesis that the hot triangle is effective for the transition to intensive combustion and the relation is effective for holding the intensive combustion respectively., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064967022, レポート番号: JAXA-SP-10-012},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {スクラムジェットエンジン内に形成される衝撃波の効果に関する考察},
 volume = {JAXA-SP-10-012},
 year = {2011}
}