@inproceedings{oai:jaxa.repo.nii.ac.jp:00046354,
 author = {髙橋, 政浩 and 富岡, 定毅 and Takahashi, Masahiro and Tomioka, Sadatake},
 book = {宇宙航空研究開発機構特別資料: 第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム (2019年7月1日-3日. 早稲田大学早稲田キャンパス国際会議場), 新宿区, 東京, 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium (July 1-3, 2019. International Conference Center, Waseda University), Shinjuku-ku, Tokyo, Japan, A flight-ground test comparison program is undergoing at JAXA to reveal so-called facility effects on hypersonic aerodynamics and combustion phenomena. The flight test vehicle will mount a combustor duct along its centerline, with so-called alligator type inlet with side-spillage to attain good starting characteristics. In the present paper, parametric study on flow-path design of the combustor model was conducted by CFD to examine influences of the geometry parameters, such as configurations of fuel injector holes and geometry of a flame-holding cavity, on combustion characteristics and to settle the design guideline which could enhance so-called vitiation effects on combustion. A two-staged fuel injection scheme was adopted for the combustor model and the first-stage and second-stage injection holes were installed at upstream and downstream of the flame-holding cavity, respectively. The results showed that a distance between the first-stage injection hole and the flame-holding cavity as well as the number of the injector holes at each stage would have strong influence on the combustor flow-field and its characteristics while the depth of the flame-holding cavity would have little influence., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1930011013, レポート番号: JAXA-SP-19-007},
 pages = {157--164},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {超音速燃焼飛行試験に用いる燃焼器流路形状の検討},
 volume = {JAXA-SP-19-007},
 year = {2020}
}