A low-diffusion robust flux splitting scheme towards wide-ranging Mach number flows  

作　　者：Shusheng CHEN Fangjie CAI Xinghao XIANG Zhenghong GAO Chao YAN 

机构地区：[1]School of Aeronautics,Northwestern Poly technical University,Xi'an 710072,China [2]AVIC The First Aircraft Institute,Xi'an 710089,China [3]China Academy of Launch Vehicle Technology,Beijing 100076,China [4]State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China [5]School of Aeronautic Science and Engineering,Beihang University,Beijing 100083,China

出　　处：《Chinese Journal of Aeronautics》2021年第5期628-641,共14页中国航空学报（英文版）

基　　金：supported by the Space Science and Technology Fund Project of China(No.2020-HT-XG-14)。

摘　　要：This paper develops a low-diffusion robust flux splitting scheme termed TVAP to achieve the simulation of wide-ranging Mach number flows.Based on Toro-Vazquez splitting approach,the new scheme splits inviscid flux into convective system and pressure system.This method introduces Mach number splitting function and numerical sound speed to evaluate advection system.Meanwhile,pressure diffusion term,pressure momentum flux,interface pressure and interface velocity are constructed to measure pressure system.Then,typical test problems are utilized to systematically assess the robustness and accuracy of the resulting scheme.Matrix stability analysis and a series of numerical cases,such as double shear-layer problem and hypersonic viscous flow over blunt cone,demonstrate that TVAP scheme achieves excellent low diffusion,shock stability,contact discontinuity and low-speed resolution,and is potentially a good candidate for wide-ranging Mach number flows.

关 键 词：Computational Fluid Dynamics(CFD) Flux splitting ACCURACY ROBUSTNESS Wide-ranging Mach number 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V411