@inproceedings{oai:jaxa.repo.nii.ac.jp:00004727,
 author = {小寺, 正敏 and 谷, 香一郎 and 植田, 修一 and Kodera, Masatoshi and Tani, Koichiro and Ueda, Shuichi},
 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, In this study, numerical calculation was conducted for the analysis of the JAXA rocket-ramjet combined cycle engine called E3, which was examined in the Ramjet Engine Test Facility (RJTF) to obtain data necessary for the engine design, under Mach 6 flight conditions. The objectives of this study are to describe flow structures inside the engine in detail and to reveal the basic working characteristics. The calculated wall pressure distributions agreed with the RJTF data, if the injected fuel flow rate was increased from the RJTF test condition. Therefore it was confirmed that the numerical calculation well duplicated the complicated flow physics inside the engine at least qualitatively. The calculation results revealed the details of the flow structures and the mixing and combustion mechanisms as follows. With fuel injection in the combustor at a total equivalence ratio of 1 including the rocket fuel, heat release due to combustion created large subsonic regions over the engine height close to the wall, while the core flow remained supersonic so that thermal choking was not achieved yet in this condition one-dimensionally. In addition, a shock train was formed in the core flow and was emanated from the position where a separation with a large recirculation zone occurred on the cowl wall. The fuel existed within the subsonic regions covered over each the wall, and as going downstream of the combustor, it concentrated at the connecting corner between the side and cowl walls. On the other hand, the supersonic air flow from the inlet was oriented toward the top wall side, resulting in forming of unburned fuel at the corner of the side and cowl walls. Then, the ignition and combustion of the injected fuel was more likely to occur around sonic lines where mixing layers were formed between the fuel and air flows. As for the engine performance, thrust augmentation due to the air-breathing combustion was almost comparable to the rocket thrust in this condition. In addition, it was found that the formation of the shock train increased the mixing and combustion efficiencies for the rocket flow, having a large impact on the thrust increase., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064967020, 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 = {マッハ６飛行条件における複合エンジン・ラムジェットモードの数値計算},
 volume = {JAXA-SP-10-012},
 year = {2011}
}