摘要
采用"亚跨超CFD软件平台"(TRIP2.0)数值模拟了DLR-F6构型,主要目的是通过计算DLR-F6构型的安装阻力考察TRIP2.0软件的数值模拟精度,并为运输机构型的气动特性计算积累经验。本文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AIAA CFD Drag Prediction Workshop Ⅱ(DPWⅡ),对比计算结果采用了CFL3D的结果。本文详细研究了网格密度、湍流模型对DLR-F6翼身组合体和翼/身/架/舱复杂组合体两种构型的的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。本文采用SST两方程模型计算两种构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影响较小。
Navier-Stokes calculation on multi-block are performed to compute drag for the DLR-F6 config- uration adopting CFD software TRIP2.0. The purpose of this paper is to validate TRIP2.0 software and gain some numerical experience of transport simulation . The structured grids（1-to-1）,test case and test data are from Drag prediction workshop II（DPWII）, the reference numerical results are obtained by CFL3D. The effects of mesh density and turbulent models to aerodynamic characters and pressure distribution are carefully studied in present paper. The results are verified by comparison with experimental data and CFL3D results. Grid refinement leads to convergence numerical results with 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 little influence on pressure distribution.
出处
《空气动力学学报》
EI
CSCD
北大核心
2009年第1期108-113,共6页
Acta Aerodynamica Sinica
