Volume 26 Issue 10
Oct.  2011
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XIANG You-zhi, ZHANG Kun-yuan, WANG Lei, GAO Xiong. Optimization design of hypersonic axisymmetric inlet with controllable law of wall pressure rise[J]. Journal of Aerospace Power, 2011, 26(10): 2193-2199.
Citation: XIANG You-zhi, ZHANG Kun-yuan, WANG Lei, GAO Xiong. Optimization design of hypersonic axisymmetric inlet with controllable law of wall pressure rise[J]. Journal of Aerospace Power, 2011, 26(10): 2193-2199.

Optimization design of hypersonic axisymmetric inlet with controllable law of wall pressure rise

  • Received Date: 2010-11-02
  • Rev Recd Date: 2011-03-31
  • Publish Date: 2011-10-28
  • The design method of axisymmetric wall boundary with a controllable law of wall pressure rise was investigated using the theory of rotational characteristics.With this design method, multi-objective optimization of the compression surface was carried out on the basis of surrogate models, and then a hypersonic axisymmetric inlet was designed using the optimal solutions.The inlet was investigated through numerical simulation, and was compared with the normal double-cone and triple-cone inlet.The results show that the length of new inlet is reduced by 32.5% of the radius than the double-cone inlet;under the design point, the performance of the new inlet lies between the double-cone and triple-cone inlet;under the start point, the flow capture ratio is improved by 8.24% and 12.60%, and the total pressure recovery is improved by 4.06% and 2.50% than the double-cone and triple-cone inlet, respectively.

     

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