摘要
采用自研的非结构网格解算器UNSMB进行了AIAA第三届阻力会议提供的DLR-F6翼身组合体的阻力计算验证。重点分析了模型的网格收敛特性、升阻力曲线以及压力分布等,并把计算结果与阻力预测会议上各个软件的计算结果以及试验数据进行比较,在此基础上分析计算结果。分析结果显示,非结构混合网格解算器的计算结果与各个软件的计算结果以及风洞试验数据吻合度较好,一定程度上验证与确认了解算器的阻力预测精度。
This paper used the unstructured grids flow solver UNSMB to have a computed verification of the drag force for the DLR – F6 wing body configuration. Selective analysis on grid convergence,lift-drag curves and pressure distribute of the wing body configuration,and compare the computing results with the results of different solversand the wind tunnel data. The analysis results showsthat the computing results ofthe unstructured grids flow solver are close to the results of different solvers and the wind tunnel data,to a certain extent it has a verification and validation forthe accuracy of computed drag of the solver.
出处
《航空计算技术》
2015年第2期84-87,95,共5页
Aeronautical Computing Technique
关键词
翼身组合体
数值模拟
计算验证
阻力计算
wing body configurations
numerical simulation
computed verification
computed drag
