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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2016, Vol. 37 ›› Issue (2): 533-544.doi: 10.7527/S1000-6893.2015.0108

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Flow characteristics of an inward turning inlet with circular outlet

WANG Weixing1,2, GUO Rongwei1   

  1. 1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. Science and Technology on Scramjet Laboratory, Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2015-01-28 Revised:2015-04-19 Online:2016-02-15 Published:2015-05-05
  • Supported by:

    Open Fund of Science and Technology on Scramjet Laboratory(STSKFKT2014002)

Abstract:

The flow characteristics of an inward turning inlet are numerically studied. The results show that at design condition, the secondary flow near the wall is induced by the cowl shock and the streamwise vortex is generated in isolator, which will cause the flow with low velocity and low total pressure to accumulate. The distribution of the aerodynamic parameters at the isolator outlet is even, which will weaken the back-pressure capacity of inlet. With angle of attack, the compression shock departs the leading edge of cowl lip and the shock wave structure changes. The middle part of the shock wave presents quasi-two-dimensional feature in the span-wise. The shock wave is weak on the two sides of compression surface and the expansion waves occur in local zone. The streamwise vortex presents in the compression section without viscosity with angle of attack, and this streamwise vortex will enhance the transfer of the flow with high total pressure from the core flow region to the wall, so the evenness of flow at the outlet of isolator is improved under viscosity.

Key words: streamwise vortex, shock wave structure, flow characteristics, inward turning inlet, numerical simulation

CLC Number: