DLR-F6翼身组合体数值计算

Drag prediction of DLR-F6 using MFlow unstructured mesh solver

使用自行研制的混合网格亚跨超声速流场解算器程序MFlow计算了AIAA第三届阻力会议提供的DLR-F6及其带整流装置FX2B情况下的阻力。重点分析了两者的网格收敛特性、阻力极曲线以及压力分布等,并与阻力会议的各个软件的计算结果进行比较。详细分析了DLR-F6翼身结合处后缘附近网格精度对分离气泡计算的影响。计算结果表明,MFlow程序的计算精度与国外软件相近,能够为阻力计算提供比较精确的结果。

Drag predictions of the DLR-F6 wing-body,with and without the FX2B fairing from the 3rd AIAA drag prediction workshop,are made using the self-made unstructured grid solver MFlow.The focus of this study are grid convergence characteristics,drag polars,and pressure distribution for the two configurations.The comparison is made between our result and the result from drag prediction workshop.The influence of flow separtion in the wing-fuselage junctions using different grids is detailed discussed.Throughout this result,the precision of our MFlow for drag prediction is similar to the CFD software,such as TAU,TAS,and USM3D,and it can be applied to drag prediction.