DLR-F6复杂组合体跨声速阻力计算研究  

Study of transonic drag computation on the DLR-F6 complex configurations

作　　者：张宏[1] 颜洪[2] 

机构地区：[1]长安大学理学院,陕西西安710064 [2]中国航空计算技术研究所航空气动力数值模拟重点实验室,陕西西安710068

出　　处：《哈尔滨工程大学学报》2013年第3期325-331,共7页Journal of Harbin Engineering University

基　　金：国家973计划资助项目(2009CB723804);国家自然科学基金资助项目(11171043);航空科学基金资助项目(20101431002)

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.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.

关 键 词：组合体 跨声速 阻力 NavierStokes方程 湍流模型 转捩 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]