基于弯曲激波压缩系统的高超声速进气道反设计研究进展

doi:10.7527/S1000-6893.2014.0240

Abstract

Abstract:

This paper gives a summary on curved shock compression research in the last decade. The new concept of curved shock compression system is proposed, in which specially designed 2D or 3D curved compression surface is applied. The leading shock wave would be curved due to its interaction with isentropic compression waves near the compression surface, and free stream is compressed by the curved shock wave together with the isentropic waves. Based on this concept: methods of reverse designing supersonic internal flow path according to assigned outflow parameters, reverse designing compression surface according to pressure distribution or Mach number distribution along the surface, and reverse designing surface according to shock wave shape are established. The curved shock compression has a good comprehensive performance as shown in the investigation, and represents a brand-new approach for the design of hypersonic propulsion compression system.

Key words: hypersonic inlet, reverse design, curved shock compression system, curved compression surface, wind tunnel test, geometry variable inlet

CLC Number:

V231

ZHANG Kunyuan. Research progress of hypersonic inlet reverse design based on curved shock compression system[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(1): 274-288.

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Research progress of hypersonic inlet reverse design based on curved shock compression system

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