Critical Transition Reynolds Number for the Incompressible Flat-plate Boundary Layer as Searched by Numerical Simulation

作     者：Yongming Zhang Di Liu Ning Li 

作者机构：Laboratory for High-Speed AerodynamicsTianjin UniversityTianjin 300072China Department of MechanicsTianjin UniversityTianjin 300072China Tianjin Key Laboratory of Modern Engineering MechanicsTianjin 300072China Research Institute of Petroleum Exploration&DevelopmentPetroChinaBeijing 100083China 

出 版 物：《Advances in Applied Mathematics and Mechanics》 (应用数学与力学进展（英文）)

年 卷 期：2023年第15卷第4期

页      面：1056-1075页

核心收录：

学科分类：07[理学] 070102[理学-计算数学] 0701[理学-数学] 

基　　金：supported by grants from the National Key Research and Development Program of China(Grant No.2016YFA0401200) the National Natural Science Foundation of China(Grant Nos.12072230,11672204,91952301,and 11732011) 

主　　题：Critical transition Reynolds number flat-plate boundary layer DNS temporal mode spatial mode 

摘      要：The critical transition Reynolds number is the lowest value at which the turbulent flow can hold in real *** determination of the critical transition Reynolds number not only is a scientific problem,but also is important for some engineering ***,there is no available theoretical method to search the critical *** the hypersonic boundary layer with significant importance for engineering problems,there is no available experimental method to search the critical value so ***,it is imperative to take numerical method to search *** this paper,direct numerical simulations(DNS)method is employed to determine the critical transition Reynolds number for the incompressible flat-plate boundary ***,under the assumption of parallel flow,the temporal mode DNS is performed to determine the critical value as Re_(xpcr)=43767,which is quite close to the numerical results of other ***,under the condition of nonparallel flow,the spatial mode DNS is performed to determine the critical transition Reynolds number as Re_(xcr)=3×10^(5),which is well consistent with the experimental *** principle,the proposed method in this paper can be extended to the supersonic/hypersonic boundary layer,and that problem will be discussed in the subsequent papers.