Flow Field and Performance Analysis of Aerospike Nozzles with Simplified Clustered Modules

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The fundamental characteristics of simplified clustered aerospike nozzles are analyzed by the computational fluid dynamics approach. Several types of aerospike nozzles, having 6, 12 and 24 inner nozzle modules with the same area ratio and total flow rate, are examined. The interactions of the exhaust flows from the neighboring modules create shock waves, which produce high-pressure regions on the nozzle surface. The base regions of the cluster-type aerospike nozzles are not influenced by the clustering of the modules and show features similar to axisymmetric-type aerospike nozzles. The base pressure is nearly equal to the environmental pressure when the pressure ratio is low and suddenly attains a constant pressure when the pressure ratio is high. The computed results show that the number of modules influence the thrust performance, and the major reason for the decrease in thrust performance with a smaller number of modules is due to thrust loss in the ramp region.

収録刊行物

  • Transactions of the Japan Society for Aeronautical and Space Sciences

    Transactions of the Japan Society for Aeronautical and Space Sciences 47(155), 17-22, 2004-05-04

    一般社団法人 日本航空宇宙学会

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各種コード

  • NII論文ID(NAID)
    10012934704
  • NII書誌ID(NCID)
    AA0086707X
  • 本文言語コード
    ENG
  • 資料種別
    ART
  • ISSN
    05493811
  • NDL 記事登録ID
    6945497
  • NDL 雑誌分類
    ZN25(科学技術--運輸工学--航空機・ロケット)
  • NDL 請求記号
    Z53-M236
  • データ提供元
    CJP書誌  CJP引用  NDL  J-STAGE 
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