TRIP2.0软件的确认:DPWⅡ复杂组合体的数值模拟  

Validation of TRIP2.0: Numerical Simulation of DPWⅡ Complex Configuration

作　　者：王运涛[1] 王光学[1] 张玉伦[1] 

机构地区：[1]中国空气动力研究与发展中心计算空气动力学研究所,四川绵阳621000

出　　处：《航空学报》2008年第1期34-40,共7页Acta Aeronautica et Astronautica Sinica

摘　　要：采用"亚跨超声速计算流体力学软件平台"(TRIP2.0)数值模拟了阻力预测小组(AIAA CFD Drag Prediction Workshop Ⅱ,DPWⅡ)翼/身/架/舱复杂组合体运输机构型,数值模拟采用的多块对接网格、测压和测力的试验结果均来自DPWⅡ,对比计算采用了CFL3D的结果。重点针对DLR-F6翼/身/架/舱复杂组合体构型,详细研究了网格密度和湍流模型对总体气动特性和压力分布的影响,计算结果与相应的试验结果取得了较好的一致。采用SA一方程和SST两方程模型均得到了网格收敛结果;不同的湍流模型对压差阻力影响较小,对摩擦阻力影响较大;不同的网格密度和湍流模型对压力分布有一定的影响。Navier-Stokes calculations on multi block are performed to compute the drag for the DLR-F6 wing/ body/pylon/nacelle configuration using CFD software TRIP2. 0. The structured grids （1-to-1）, test case and test data are from Drag Prediction Workshop Ⅱ （DPW Ⅱ ）, and the reference numerical results are obtained by CFL3D. The effects of mesh density and turbulent models on the aerodynamic characters and pressure distributions are carefully studied. The results are verified in comparison with the test data and CFL3D results. Grid refinement leads to convergences of the numerical results with both SA and SST turbulent models. It is demonstrated that various turbulent models have little influence on pressure drag, whereas obvious influence on friction drag is observed, and various turbulent models and grids have some influence on pressure distribution.

关 键 词：空气动力学 数值模拟 阻力 湍流模型 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]