中文摘要：

为了考察阻力预测的准确性,评估挂架/吊舱引起的阻力增量,分析网格和转捩对阻力及阻力增量的影响,采用不同密度网格,对DLR-F6翼/身和翼/身/挂/舱组合体跨声速流场进行了全湍流和固定转捩2种方式的数值模拟.翼/身和翼/身/挂/舱组合体均得到了网格收敛性结果,机翼表面和吊舱表面压力分布与实验数据吻合良好.预测的阻力增量高出实验数据0.000 3,优于其他软件的结果.网格细分对壁面压力分布影响较小,对阻力尤其是压差阻力影响较大;相对于全湍流,转捩对阻力尤其是摩擦阻力影响较大,对挂架/吊舱引起的阻力增量几乎没有影响.

英文摘要：

The accuracy of the drag prediction was investigated by simulating the transonic flow fields around the DLR-F6 wing-body（WB） and wing-body-nacelle-pylon（WBNP） configurations.The computations were performed using fully turbulence boundary-layer and fixed position transition boundary-layer respectively.Multiple sets of grids with different densities were then employed.The drag,drag increments by adding the nacelle and the pylon and the effects of grid and transition were also estimated.The results show that grid refinement leads to convergent results for two configurations,and the predicted surface pressure distributions on the wing and nacelle are in agreement with the experimental data.When comparing the experiment data,the predicted incremental drag was over estimated by about 3 drag counts,0.000 3,but better than the results obtained by using other software.The computed results show that grid refinement had little effect on the wall surface pressure distributions,but obvious effect on drag,especially the pressure drag.Relative to the whole turbulence model,transition had obvious effect on drag,particularly on friction drag,but almost no effect on nacelle/pylon induced incremental drag.