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
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
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45301&item_no=1&attribute_id=31&file_no=1
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）
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