Abstract: 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.