Based on the model containing wing, body and nacelle, the Reynolds-averaged Navier-Stokes equations were solved using patched grid and multiple reference frames (MRF) method to simulate the configuration with different wing plain-form. The results show that the configuration with better aerodynamic performance will improve the whole lift-to-drag ratio for 3. 6％. Comparing the force coefficients for every parts among all configurations, pressure coefficient distribution along specific wing section and flow structures in flow field, the mechanism through which the better configuration will enhance the performance is revealed. It shows that prolong the wing section after slipflow and reduce the chord of outboard wing will increase the lift-to-drag ratio, and the main reason is that not only the configuration will exploit the accelerating effect of slipflow but it will reduce the separation on the wing remarkably.%以带螺旋桨的翼身-短舱组合体为几何模型,采用基于拼接网格技术及多重参考系(MRF)方法求解雷诺平均Navier-Stokes(RANS)方程,对在螺旋桨滑流作用下的不同机翼平面形状构型进行数值模拟,得到了气动性能更好的机翼平面形状,全机升阻比相对于原始构型提高了3.6％.通过对比不同构型中各部件的力系数,机翼上特征站位的压力系数分布曲线以及流场结构特征,找出了在滑流影响下这种机翼平面形状使其气动性能提高的机理.结果表明:增加滑流区域的机翼弦长并减少非滑流区域的机翼弦长能够增加机翼的升阻比,其主要机理在于这种布局能够充分利用滑流的加速效应,并减小机翼上表面的气流分离.
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