A Comparison of Scramjet Engine Performances of Various Cycles

• 資料種別: 文書・図像類
• タイトル: A Comparison of Scramjet Engine Performances of Various Cycles
• 著者・編者: 苅田, 丈士; 升谷, 五郎; 若松, 義男; 鎮西, 信夫; 冠, 昭夫; KANDA, Takeshi; MASUYA, Goro; WAKAMATSU, Yoshio; CHINZEI, NOBUO; KANMURI, Akio
• 著者標目: 苅田, 丈士; 升谷, 五郎; 若松, 義男; 鎮西, 信夫; 冠, 昭夫; KANDA, Takeshi; MASUYA, Goro; WAKAMATSU, Yoshio; CHINZEI, NOBUO; KANMURI, Akio
• 出版事項: 航空宇宙技術研究所
• 出版年月日等: 1989-11
• 出版年（W3CDTF）: 1989-11
• 並列タイトル等: スクラムジェットエンジンサイクル性能比較
• タイトル（掲載誌）: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1042
• 巻号年月日等（掲載誌）: 1042
• 掲載巻: 1042
• 掲載ページ: 14-
• ISSN（掲載誌）: ISSN : 0389-4010
• 本文の言語コード: eng
• 対象利用者: 一般
• 一般注記: Assuming an airframe-integrated hydrogen fueled scramjet engine, we compared the performances of engines of various engine cycles : an expander cycle, a staged combustion cycle, a coolant bleed cycle, and a gas generator cycle. Each engine was regeneratively cooled by liquid hydrogen. Effects of flight Mach number, flight dynamic pressure, and fuel injection to air dynamic pressure ratio were examined as related to the power balance of the propellant feed line. It follows that the system pressure of the closed loop cycle increases and the specific impulse of the open loop cycle decreases with increasing flight Mach number, flight dynamic pressure, or fuel injection to air dynamic pressure ratio, i.e., with increasing fuel injector manifold pressure. Of the four cycles, the coolant bleed cycle shows well balanced engine performance, keeping the system pressure within a reasonable range.; 資料番号: NALTR1042000; レポート番号: NAL TR-1042
• オンライン閲覧公開範囲: 限定公開
• 連携機関・データベース: 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）; https://irdb.nii.ac.jp
• 提供元機関・データベース: 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ