並列タイトル等Experimental Study of Zero-Secondary-Flow Ejectors for Rocket Engine Altitude Simulation
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-449
一般注記Ejector characteristics tests and detailed diffuser wall pressure measurements were made on six basic zero secondary flow ejector configurations, which were combinations of two different area ratio nozzles and three diffusers. One constant area diffuser and two second throat diffusers with different contraction area ratios were used. In each configuration, a diffuser was attached to a vacuum capsule in which a simulated rocket engine nozzle driven by cold nitrogen gas was set up. It is shown that over a certain range of nozzle exit position XNE relative to the second throat diffuser inlet plane, a minimum capsule pressure ratio Pc/Pt is maintained and that the optimum position, i.e., the nozzle exit position where minimum starting or break down system pressure ratio Pt/Pa is minimum, is somewhere in the capsule region. A further withdrawal of the nozzle into the capsule region produces an increase in capsule pressure ratio which is approximately linear with XNE. In a better performing configuration, the length of separated flow region is shorter for the same system pressure ratio. The starting characteristics data and second throat ramp pressures are compared with the calculation using the approximate method of German, et al., and it is shown that the method predicts generally satisfactory trends when the relative position of nozzle and diffuser is appropriate.
資料番号: NALTR0449000
レポート番号: NAL TR-449
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