Direct numerical simulation of hypersonic transition induced by an isolated cylindrical roughness element

作     者：DUAN Zhi Wei XIAO Zhi Xiang FU Song 

作者机构：School of Aerospace Tsinghua University 

出 版 物：《Science China(Physics,Mechanics & Astronomy)》 (中国科学：物理学、力学、天文学（英文版）)

年 卷 期：2014年第57卷第12期

页      面：2330-2345页

核心收录：

学科分类：080103[工学-流体力学] 08[工学] 080104[工学-工程力学] 0825[工学-航空宇航科学与技术] 0801[工学-力学（可授工学、理学学位）] 

基　　金：supported by the National Natural Science Foundation of China(Grant No.11372159) 

主　　题：hypersonic boundarry layer transtion roughness 

摘      要：Hypersonic boundary layer transition induced by an isolated cylindrical roughness element is investigated using direct numerical simulation method based on a finite volume *** simulate the transition procedure by resolving the generation and evolvement of small-scale coherent structures,and capture the shock wave at the same time,high-order minimum dispersion and controllable dissipation scheme is validated and then *** results are compared with the available measurements in the quiet wind tunnel,such as the dominated frequency and root mean square of *** computational dominated frequency of 19.23 k Hz is very close to the experimental one,21 k ***,the disturbances of the roughness are mostly generated by thejetjust before the roughness,and then they travel and develop downstream with the shear layer and vortex *** transition is mainly dominated by the instabilities of both the horseshoe vortex and the shear layer.