粗糙元诱导的高超声速边界层转捩
收稿日期: 2016-01-18
修回日期: 2016-04-26
网络出版日期: 2016-04-29
基金资助
国家自然科学基金（11372159）；中国博士后科学基金（2015M571029）；国家重点研发计划项目（2016YFA0401200）
Roughness element induced hypersonic boundary layer transition
Received date: 2016-01-18
Revised date: 2016-04-26
Online published: 2016-04-29
Supported by
National Natural Science Foundation of China (11372159);China Postdoctoral Science Foundation (2015M571029);National Key Research and Development Project (2016YFA0401200)
段志伟 , 肖志祥 . 粗糙元诱导的高超声速边界层转捩[J]. 航空学报, 2016 , 37(8) : 2454 -2463 . DOI: 10.7527/S1000-6893.2016.0130
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.
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