Volume 22 Issue 2
Feb.  2007
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XU Hua-song, GU Liang-xian. Nozzle afterbody design of hypersonic flight vehicle[J]. Journal of Aerospace Power, 2007, 22(2): 257-260.
Citation: XU Hua-song, GU Liang-xian. Nozzle afterbody design of hypersonic flight vehicle[J]. Journal of Aerospace Power, 2007, 22(2): 257-260.
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Nozzle afterbody design of hypersonic flight vehicle

  • Shool of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China

  • Received Date: 2005-12-28
  • Rev Recd Date: 2006-10-25
  • Publish Date: 2007-02-28
    Abstract
  • A model based on numerical solution of Navier-Stokes equations was established for hypersonic flight vehicle nozzle afterbody optimization design.The internal portion and the upper wall of nozzle were designed,and the optimized configuration was obtained.The result was compared to the norm configuration that Edwards claimed.The results show that the performance of nozzle afterbody was improved.

     

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    • References(4)
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    Edwards C L Q,Small W J,Weidner J P.Studies of scramjet/airframe integration techniques for hyper-sonic aircraft[R].AIAA-75-58.
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    潘锦珊.气体动力学基础[M].北京:国防工业出版社,1988.
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