Volume 28 Issue 4
Apr.  2013
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ZHANG Lin, ZHANG Kun-yuan, WANG Lei, LIU Yuan. Computational investigation of hypersonic curved shock two-dimensional inlet with compression surface constant Mach number gradient[J]. Journal of Aerospace Power, 2013, 28(4): 752-758.
Citation: ZHANG Lin, ZHANG Kun-yuan, WANG Lei, LIU Yuan. Computational investigation of hypersonic curved shock two-dimensional inlet with compression surface constant Mach number gradient[J]. Journal of Aerospace Power, 2013, 28(4): 752-758.

Computational investigation of hypersonic curved shock two-dimensional inlet with compression surface constant Mach number gradient

  • Received Date: 2012-05-07
  • Publish Date: 2013-04-28
  • A type of curved compression surface with wall Mach number linear distribution was investigated,and a hypersonic curved shock two-dimensional inlet was designed.The performance was compared with normal three-ramp compression inlet designed under the same conditions.The result shows that:curved compression surface can be designed through rational characteristic linear theory according to the given wall Mach number linear distribution and pressure ratio.Compared with normal three-ramp compression,the new inlet has more stable boundary layer and much shorter external compression surface,but not very sensitive to the change of free stream Mach number.Especially,the inlet has an excellent performance under off-design conditions.The mass flow rate reaches 0.783 at relay point Mach number and is increased by 13.2% compared to normal three-ramp compression two-dimensional inlet, while the total pressure recovery of throat section is also increased by 4.5%.

     

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