半展长襟翼梯形翼构型数值模拟技术研究

基于雷诺平均的 Navier-Stokes 方程和拼接结构网格技术,采用 MUSCL 格式和 SST 湍流模型,研究了网格密度对半展长襟翼梯形翼高升力构型的数值模拟结果的影响。相应的风洞试验是1998年在 NASA Ames 12英尺增压风洞(PWT)中完成的,试验结果包括了总体气动特性、压力分布。研究内容主要包括网格密度对收敛历程、气动力特性、压力分布和表面流线的影响,以及气动力特性随迎角的变化。研究表明,Ma=0.15,α=16.7°时,网格密度对收敛历程、典型站位压力分布和表面流态基本没有影响,气动力特性随网格密度单调变化；采用不同密度的网格,典型剖面的压力分布与试验结果吻合良好；与修正后的试验数据相比较,数值模拟得到的失速迎角前的气动力系数与试验结果吻合良好。

Numerical simulation of the part-span flap trap wing configuration

Based on the Reynolds-averaged Navier-Stokes(RANS)equations and structured grid (surface to surface)technique,the effect of different grid density on simulation results of a part-span trap wing configuration is analyzed with MUSCL scheme and SST turbulent model. The corresponding experiment was accomplished in NASA Ames 12′PWT in 1 998,the experi-mental data included the aerodynamic characters and pressure distribution The presented research work includes the influence of grid density on convergence history,aerodynamic character,pres-sure distribution and surface streamlines.The variation of aerodynamic characters with the angles of attack is also presented on the medium grid.The numerical results indicate that the grid densi-ty has little influence on convergence history,pressure distribution and surface streamlines at the conditions of Ma =0.15,α=1 6.7°,and the aerodynamic characters vary monotonously with the grid density.Compared with experimental data,the numerical pressure distributions with differ-ent grids are quite reasonable at the typical span sections,the numerical aerodynamic characteris-tics on the medium grid are in good agreement with corrected experimental data before stall.