作　　者： ; ; ;

机构地区： 西北工业大学动力与能源学院翼型叶栅空气动力学国防科技重点实验室

出　　处： 《西北工业大学学报》 2014年第2期169-175,共7页

摘　　要： 通过数值模拟和理论分析的综合研究,比较了网格密度不同对计算的影响,研究了中心格式和3种迎风格式(AUSM+格式、AUSM+up格式、Roe格式)的计算性能,探讨了壁面温度变化对气动力/气动热计算的影响。结果表明:网格密度变化对气动力计算影响不大,但却在很大程度上影响热流的计算及流动分离的模拟;各空间格式都能准确地计算出流场压力分布,有较高的激波分辨率,但鲁棒性有所差异,其中AUSM+up格式在高超声速流场计算中鲁棒性较好;壁面温度升高会导致所得分离区增大,气动力/气动热分布也会相应发生变化;在分离区后的流动再附会很大程度上增大该区域的热流值。 Hypersonic flow field has been numerically investigated for two different configurations, to study the aer-odynamic / aero-thermal effects. Simulations were performed using an in-house hybrid unstructured Reynolds-aver-aged Navier-Stokes solver （ HUNS3D） . Four different flux differencing schemes （ central scheme and three upwind schemes AUSM＋, AUSM＋up, Roe） were employed for spatial discretization. The accuracy of all the schemes was compared with each other and with the available experimental data. Different levels of meshes were generated to in-vestigate the effect of grid resolution. The pressure distribution was not much influenced by the mesh resolution;however the predicted heat flux was greatly affected by the change in the mesh resolution. The shock position has been accurately captured by the Central, AUSM＋and AUSM＋up schemes. The predicted pressure distribution was in good agreement with the experimental data but some difference was observed in the robustness of flux differencing schemes. The increase in the wall temperature gives rise to flow separation which eventually affects the aerodynamic/ aero-thermal heating. After the separation zone the flow reattachment enhances the surface heat transfer dramatic-ally.

关 键 词： 高超声速 数值模拟 气动力 气动热 网格 空间离散格式 壁面温度

领　　域： [航空宇航科学与技术] [航空宇航科学技术]