AUSM+格式在高超声速进气道数值模拟中的应用  

Application of AUSM+Scheme in Numerical Simulation of Hypersonic Inlet

作　　者：杜磊[1] 孙波[1] 代春良 Du Lei;Sun Bo;Dai Chunliang(Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学,江苏南京210094

出　　处：《航空科学技术》2020年第11期120-126,共7页Aeronautical Science & Technology

摘　　要：基于开源计算流体力学软件OpenFOAM中的密度基求解器rhoCentralFoam植入典型混合格式AUSM+。求解器通过两组算例进行验证:二维圆柱绕流数值模拟和二维高超声速进气道数值模拟。与圆柱绕流模型相似的高超声速进气道钝化前缘,是高超声速进气道典型流动特征。数值计算结果分别与商业软件CFD++计算结果和试验结果进行对比,结果表明,基于OpenFOAM植入的AUSM+格式可以精确捕捉脱体激波、准确构建流场结构,并得到可靠的流场参数,与商业软件CFD++计算结果和试验结果均具有良好的一致性,满足高超声速进气道流场计算需求。Based on the density-base solver rhoCentralFoam of open source computational fluid dynamics(CFD)software OpenFOAM,a typical hybrid scheme AUSM+is implemented.The solver is verified by two sets of numerical examples:numerical simulation of the flow around the two-dimensional cylinder;numerical simulation of the twodimensional hypersonic inlet.The blunted leading edge of the hypersonic inlet,which is similar to the cylindrical flow model,is a typical flow characteristic of the hypersonic inlet.The numerical calculation results are compared with the commercial software CFD++calculation results and experiment data respectively.The results show that the AUSM+scheme based on OpenFOAM can capture the detached shock wave accurately,construct the flow field structure accurately and obtain the reliable flow field parameters.The results are in agreement with the commercial software CFD++calculation results and experimental results,and satisfy the caculation requirements of hypersonic inlet flow field.

关 键 词：高超声速流动 OPENFOAM AUSM+ 通量分裂 数值模拟 

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]