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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2016, Vol. 37 ›› Issue (8): 2445-2453.doi: 10.7527/S1000-6893.2016.0200

• Numerical Simulation Investigations of Unsteady Flow • Previous Articles     Next Articles

Large eddy simulation for forced transition flow at hypersonic inlet

ZHAO Xiaohui1, DENG Xiaobing1, MAO Meiliang2, YANG Wei1, ZHAO Huiyong3   

  1. 1. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China;
    2. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China;
    3. Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2016-02-16 Revised:2016-06-21 Online:2016-08-15 Published:2016-06-27
  • Supported by:

    National Natural Science Foundation of China (11402289)

Abstract:

Forced transition is commonly used for a hypersonic air breathing vehicle to ensure its scramjet's normal start by placing roughness elements or vortex generators in the inlet boundary layer. To get a clear image of forced transition process, an implicit large eddy simulation method is used for laminar-turbulent forced transition flows in the boundary layer of a hypersonic inlet configuration. Main structures are obtained for the forced transition flows induced by the vortex generators shaped of diamonds and ramps, which show that the flows are dominated by stream-wise counter-rotating vortices. Fluctuations grow in the stream-wise direction and cause instabilities. Two fundamental modes of the instabilities are found in the simulations, the even mode and the odd one. The even mode leads to a varicose way of breaking down of the counter-rotating vortices, while the odd one leads to a sinuous way. Strings of hairpin vortices are generated after the breaking down and finally cause the transition. A discussion is carried out on the computation convergence together with the influence of the grids and numerical dissipation.

Key words: hypersonic, inlet, forced transition, vortex generator, large eddy simulation

CLC Number: