锯齿形转捩片触发高超声速进气道边界层转捩的大涡模拟

doi:10.7527/S1000-6893.2019.22930

Abstract

Abstract: To promote the application of zig-zag trip in hypersonic inlet, a high-precision large eddy simulation method is used to examine the boundary layer transition triggered by zig-zag trip on three-stage compression wedge of two-dimensional inlet in wind tunnel. The numerical method is based on the implicit subgrid-scale model. The high-precision flux-limited compact scheme is used for spatial discretization and the explicit Runge-Kutta method for time marching. The numerical simulation clearly captures the spatial evolution process of boundary layer transition, and obtains the statistical mean flow field and fluctuation characteristics. The numerical simulation results show that the zig-zag trip can effectively trigger the boundary layer transition. By comparing the numerical simulation results with those of isentropic compression surface and single wedge surface, the mechanism of boundary layer transition is obtained and lays a foundation for further study.

Key words: hypersonic, inlet, zig-zag trip, large eddy simulation, transition mechanism

CLC Number:

V211.3

ZHANG Hongjun, ZHU Zhibin, SHANG Qing, LIU Zhiyong, SHEN Qing. Large eddy simulation of hypersonic inlet boundary layer transition triggered by zig-zag trip[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(10): 122930-122930.

References 29

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Large eddy simulation of hypersonic inlet boundary layer transition triggered by zig-zag trip

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