Volume 26 Issue 11
Nov.  2011
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Article Navigation >  Journal of Aerospace Power  > 2011  >  26(11): 2556-2562
ZHANG Lin, ZHANG Kun-yuan, WANG Lei, NAN Xiang-jun, XIANG You-zhi. Preliminary study on hypersonic curved shock two-dimensional inlet[J]. Journal of Aerospace Power, 2011, 26(11): 2556-2562.
Citation: ZHANG Lin, ZHANG Kun-yuan, WANG Lei, NAN Xiang-jun, XIANG You-zhi. Preliminary study on hypersonic curved shock two-dimensional inlet[J]. Journal of Aerospace Power, 2011, 26(11): 2556-2562.
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Preliminary study on hypersonic curved shock two-dimensional inlet

  • Received Date: 2010-12-15
  • Rev Recd Date: 2011-04-23
  • Publish Date: 2011-11-28
    Abstract
  • A type of curved compression surface with certain wall pressure distribution was investigated,and a hypersonic curved shock two-dimensional inlet was designed.The performance was compared through numerical simulation with normal hypersonic three-wedge and wedge-isentropic two-dimensional inlets under the same conditions.The result shows:the curved shock inlet with more stable boundary layer can be designed according a proper wall pressure distribution;the inlet can be shortened by 12% and 10%,respectively,as compared with three-wedge inlet and wedge-isentropic inlet,and is not very sensitive to the change of free stream Mach number;the new inlet has obvious superiority on the overall performance and bright prospect in the applications.

     

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