DLR-F6翼身组合体的高阶精度数值模拟
收稿日期: 2014-09-07
修回日期: 2014-12-29
网络出版日期: 2015-01-07
基金资助
国家重点基础研究发展计划 (2014CB744803)
High-order accuracy numerical simulation of DLR-F6 wing-body configuration
Received date: 2014-09-07
Revised date: 2014-12-29
Online published: 2015-01-07
Supported by
National Key Basic Research Program of China (2014CB744803)
基于雷诺平均Navier-Stokes(RANS)方程和结构网格技术,采用五阶空间离散精度的加权紧致非线性格式(WCNS)和剪切应力输运(SST)两方程湍流模型,开展了DLR-F6翼身组合体的高阶精度数值模拟研究。主要目的是确认WCNS模拟跨声速典型运输机构型的能力。采用粗、中、细3套网格开展了网格收敛性研究,从气动特性、压力分布、表面流态等方面研究了网格密度对DLR-F6翼身组合体气动特性的影响;采用中等网格开展了来流迎角对气动特性的影响研究。通过与试验数据、CFL3D软件和TRIP软件计算结果的对比,表明网格密度主要影响激波位置和压差阻力系数,同时对翼身结合部分离区大小有一定影响;采用高阶精度计算方法显著提高了气动力系数的模拟精度,力矩系数数值模拟结果与试验的差异有待进一步分析。
王运涛 , 孙岩 , 王光学 , 张玉伦 , 李伟 . DLR-F6翼身组合体的高阶精度数值模拟[J]. 航空学报, 2015 , 36(9) : 2923 -2929 . DOI: 10.7527/S1000-6893.2014.0362
Based on the Reynolds-averaged Navier-Stokes (RANS) equations and structured grid technology, the fifth-order weighted compact nonlinear scheme (WCNS) and shear stress transport (SST) turbulence model are adopted to conduct a high-order numerical simulation of DLR-F6 wing-body configuration, for the purpose of validating the ability of WCNS in the simulation of typical transport configuration at transonic speed. The grid convergence study is performed with coarse, medium and fine grid systems, the effects of grid density on the simulation of DLR-F6 wing-body configuration are studied from aerodynamic characteristics, pressure distribution and flow pattern on the surface. The variation of aerodynamic characteristics with angles of attack is performed with the medium grid. Compared to the experimental data, CFL3D and TRIP results, the numerical results indicate that the grid density mainly affect the location of shock wave and pressure drag coefficient, and slightly affect the size of separation zone at the wing-body juncture. The numerical accuracy is significantly improved with high-order numerical method and the discrepancy of pitching moment coefficients between numerical data and experimental data needs further study.
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