双缝襟翼缝道参数气动影响敏感度研究与设计

针对后缘双缝襟翼,采取先后缝再前缝的缝道参数设计方法,通过数值计算分析和风洞试验验证研究了襟翼偏角、缝道宽度、重叠量对增升效率的影响规律。采用点对点链接多块结构网格技术,通过求解RANS方程对缝道流场进行数值计算,结果表明:后缝道宽度对升力系数、阻力系数影响较缝道重叠量大,为更敏感参数;前缝道重叠量对升力系数、阻力系数影响较缝道宽度大,属更敏感参数。结合上述设计方法与数值计算工具,高效、准确地确定了较优的二维襟翼剖面参数,且襟翼效率计算结果与风洞试验结果吻合较佳,可为同类飞机增升装置设计提供参考和借鉴。

Stuty and design on double-slotted flap parameters for aerodynamic sensitivity

Adopting one method of slot design which is firstly the rear slot design then the front, the influence of deflection, slot gap and overlap on lift enhancing efficiency has been studied based on numerical calculation and wind tunnel test for trailing-edge double-slotted flap.Adopting point-to-point link multi-block grid technology, a numerical simulation of flow has been accomplished field by solving the discrete Reynolds Average Navier-Stokes Equation. The results show that, the influence of the front slot gap on lift coefficient and drag coefficient is large than overlap, which is a more sensitive parameter, and the influence of the front slot overlap on lift coefficient and drag coefficient is large than gap, which is a more sensitive parameter. The optimal slot parameters of double-slotted flap has been efficiently and accurately designed using this method and numerical calculation toll, which can provide reference for similar aircraft lift device design.