粗糙元诱导的高超声速边界层转捩

doi:10.7527/S1000-6893.2016.0130

Abstract

Abstract:

Hypersonic boundary layer transition from laminar to turbulent induced by different isolated roughness elements is investigated using direct numerical simulation based on finite volume formulation. To explore the transition mechanism through resolving the small flow structure, and capture shock wave in hypersonic flow, the high order minimized dispersion and controllable dissipation (MDCD) scheme is used to reconstruct the convection terms of Navier-Stokes equations. The numerical results agree well with experimental data. The numerical method adopted in this article is able to resolve small flow structures and their break-up and instability procedure. And it shows that the transition is dominated by the instability of the three-dimensional shear layer on top of the roughness elements. The effect of roughness element shape and geometrical parameters on transition mechanisms, and the transition results of multiple roughness elements are quantitatively studied.

Key words: hypersonic, roughness element, boundary layer transition, parameter effects, direct numerical simulation

CLC Number:

V211.3

DUAN Zhiwei, XIAO Zhixiang. Roughness element induced hypersonic boundary layer transition[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(8): 2454-2463.

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Roughness element induced hypersonic boundary layer transition

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