Volume 25 Issue 12
Dec.  2010
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YUAN Hua-cheng, GUO Rong-wei. High enthalpy wind tunnel tests of hypersonic inlets with rectangular section[J]. Journal of Aerospace Power, 2010, 25(12): 2748-2755.
Citation: YUAN Hua-cheng, GUO Rong-wei. High enthalpy wind tunnel tests of hypersonic inlets with rectangular section[J]. Journal of Aerospace Power, 2010, 25(12): 2748-2755.

High enthalpy wind tunnel tests of hypersonic inlets with rectangular section

  • Received Date: 2010-01-24
  • Rev Recd Date: 2010-06-10
  • Publish Date: 2010-12-28
  • Preliminary test study was conducted for hypersonic inlets with rectangular section at Mach number of 6,5 and 4 in a high enthalpy wind tunnel.The inlet could be started within the range of the Mach number 4.5 and 6.5.The performance and static-pressure distributions of the inlet under different back-pressure conditions were obtained.Results indicate that,at design condition(Ma=6,α=0°),the mass flow capture rate and mass-averaged total pressure recovery coefficient are 0.97 and 0.41,respectively;at the exit section of the isolator,the average Mach number is less than 2.6,the pressure rise and maximum back-pressure are 35 and 141.52 times of upstream pressure.The shock train formed by back-pressure rising can be kept in the inner tunnel,without affecting the mass flow capture rate.The mass flow capture rate is not less than 0.77,and the mass-averaged total pressure recovery coefficient varies between 0.49 and 0.67 at Mach number of 5 and 0° angle of attack.In the non-back-pressure status,there is no obvious flow separation in the flow inlet field of the inlet.

     

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