缝道参数对多段翼型气动性能的影响  

Influence of gap parameters on aerodynamics of multi-element airfoil

作　　者：秦绪国[1] 刘沛清[1] 屈秋林[1] 彭国辉[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《北京航空航天大学学报》2011年第2期193-196,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家973重点基础研究发展计划(2009CB72400101);"凡舟"青年科研基金资助项目(20090504)

摘　　要：数值模拟研究缝道参数对着陆构型多段翼型气动性能的影响,采用有限体积法求解雷诺平均N-S(Navier-Stokes)方程,湍流模型采用S-A(Spalart-Allmaras)模型,给出了多段翼型升力系数与表面压力系数随各缝道参数的变化规律.计算结果表明:采用的计算模型可用于二维多段翼型的计算;缝道参数对多段翼型气动性能的影响显著,在各个缝道参数的变化范围内升力系数均存在最优值,适当的缝道参数可以抑制后翼上表面逆压梯度,消除后翼分离,并保持前翼尾迹不与后翼边界层相掺混,提高多段翼型的气动性能.The effect of flap and slat riggings on the multi-element airfoil was investigated numerically.The compressible Navier-Stokes equations were solved by the finite-volume method.Spalart-Allmaras（S-A） turbulence model was used.The effects of flap and slat riggings on lift coefficients and pressure coefficients were provided.The validation of computation agreed well with the experimental results.The computations on the effect of flap and slat riggings shows that lift coefficient has an optimum with every design parameter.With proper flap and slat riggings,the adverse pressure gradient and the separation on the backward wing section could be suppressed,and the wake from forward wing section does not mix with the boundary layer of backward wing section.So the performance of the airfoil can be improved.

关 键 词：数值模拟 多段翼型 缝道参数 气动特性 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]