@inproceedings{oai:jaxa.repo.nii.ac.jp:00002934,
 author = {川﨑, 央 and 笠原, 次郎 and 稲川, 智也 and 松岡, 健 and 川島, 秀人 and 松尾, 亜紀子 and 船木, 一幸 and Kawasaki, Akira and Kasahara, Jiro and Inakawa, Tomoya and Matsuoka, Ken and Kawashima, Hideto and Matsuo, Akiko and Funaki, Ikko},
 book = {宇宙航空研究開発機構特別資料: 第50回流体力学講演会/第36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 50th Fluid Dynamics Conference / the 36th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム (2018年7月4日-6日. 宮崎市民プラザ), 宮崎市, 宮崎, 50th Fluid Dynamics Conference /the 36th Aerospace Numerical Simulation Symposium (July 4-6, 2018. Miyazaki Citizen's Plaza), Miyazaki, Japan, In this study, an inner-cylinder-replaceable rotating detonation rocket engine is tested in a vacuum environment for various inner-cylinder radii r(sub i) ranging from 31 mm (typical lab scale) to 0 mm (no inner cylinder). As a result, it was clarified that there exists a critical inner-cylinder radius to sustain adequate thrust performance in the engine. Detonation waves attached to the inner-cylinder wall for r(sub i) = 23 and 31 mm (supercritical cases), whereas detachment of detonation waves from the inner-cylinder wall was observed for r(sub i) = 0 and 9 mm (subcritical cases), and 15 mm (critical case). In the cases of r(sub i) = 0, 9 mm (subcritical), and 15 mm (critical), strong chemical luminescence was observed significantly in the exhaust plume. For r(sub i) = 15 mm (critical cases), and 23 and 31 mm (supercritical cases), the measured specific impulses were greater than 80% of theoretical values. However, for r(sub i) = 0 and 9 mm (subcritical cases), the measured specific impulses were below 80% of the theoretical values. This is to be attributed to the imperfect detonation combustion observed significantly in the subcritical cases. From these results, we have concluded that the inner-cylinder radius is, at 15 mm, close to the critical condition to keep rotating detonation waves in a favorable state in the combustor., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1830029005, レポート番号: JAXA-SP-18-005},
 pages = {91--95},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {回転デトネーションロケットエンジンの内筒が推力性能に与える影響に対する実験的検討},
 volume = {JAXA-SP-18-005},
 year = {2019}
}