Hypersonic Shock Wave/Boundary Layer Interactions by a Third-Order Optimized Symmetric WENO Scheme  

作　　者：Li Chen Guo Qilong Li Qin Zhang Hanxin 

机构地区：[1]State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, P. R. China [2]Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, P. R. China

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2017年第5期524-534,共11页南京航空航天大学学报（英文版）

基　　金：supported by the National Key Basic Research and Development Program (No.2014CB744100)

摘　　要：A novel third-order optimized symmetric weighted essentially non-oscillatory(WENO-OS3)scheme is used to simulate the hypersonic shock wave/boundary layer interactions.Firstly,the scheme is presented with the achievement of low dissipation in smooth region and robust shock-capturing capabilities in discontinuities.The Maxwell slip boundary conditions are employed to consider the rarefied effect near the surface.Secondly,several validating tests are given to show the good resolution of the WENO-OS3 scheme and the feasibility of the Maxwell slip boundary conditions.Finally,hypersonic flows around the hollow cylinder truncated flare(HCTF)and the25°/55°sharp double cone are studied.Discussions are made on the characteristics of the hypersonic shock wave/boundary layer interactions with and without the consideration of the slip effect.The results indicate that the scheme has a good capability in predicting heat transfer with a high resolution for describing fluid structures.With the slip boundary conditions,the separation region at the corner is smaller and the prediction is more accurate than that with no-slip boundary conditions.A novel third-order optimized symmetric weighted essentially nomoscillatory （WENO-OS3） scheme is used to simulate the hypersonic shock wave/boundary layer interactions. Firstly, the scheme is presented with the achievement of }.ow dissipation in smooth region and robust shock-capturing capabilities in discontinuities. The Maxwell slip boundary conditions are employed to consider the rarefied effect near the surface. Secondly, several validating tests are given to show the good resolution of the WENO OS3 scheme and the feasibility of the Maxwell slip boundary conditions. Finally, hypersonic flows around the hollow cylinder truncated flare （HCTF） and the 250/55~ sharp double cone are studied. Discussions are made on the characteristics of the hypersonic shock wave/ boundary layer interactions with and without the consideration of the slip effect. The results indicate that the scheme has a good capability in predicting heat transfer with a high resolution for describing fluid structures. With the slip boundary conditions, the separation region at the corner is smaller and the prediction is more accurate than that with no slip boundary conditions.

关 键 词：hypersonic flows shock wave/boundary layer interactions weighted essentially non-oscillatory(WENO)scheme slip boundary conditions 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]