Summary of code validation results for a multiple element airfoil test case
Summary of code validation results for a multiple element airfoil test case
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多元件翼型测试用例的代码验证结果摘要
DOI：
10.2514/6.1997-1932
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发表时间：
1997
期刊：
影响因子：
--
通讯作者：
I. Fejtek
中科院分区：
文献类型：
--
作者：
I. Fejtek
本文总结了在起飞构型多段翼型上进行的计算机程序验证工作。代码范围从面板和全位势方法结合积分边界层方法，不可压缩和可压缩的Navier-Stokes求解器。本次基准测试的十位参与者代表政府实验室、工业界和学术界。将升力、阻力和俯仰力矩以及表面压力和总压分布的计算值与实验测量值进行比较。对代码的CPU和内存要求进行了比较。结果分析表明，除了湍流建模，解决网格的影响，过渡和远场边界条件的问题可以有显着的影响解决方案的精度。
A summary of a computer code validation exercise performed on a multiple element airfoil in takeoff configuration is presented. The codes range from panel and full potential methods combined with integral boundary layer methods, to incompressible and compressible Navier-Stokes solvers. The ten participants in this benchmarking exercise represent government laboratories, industry, and academia. Computed values of lift, drag, and pitching moment, as well as surface pressures and total pressure profiles are compared with experimental measurements. The CPU and memory requirements of the codes are compared. An analysis of the results shows that in addition to turbulence modeling, addressing the issues of grid influence, transition, and farfield boundary conditions can have a significant impact on solution accuracy.