前掠角对串置翼模型升阻特性影响分析

Analysis of Influence of Forward Swept Angle on Lift-Drag Characteristics of Tandem Wing Model

为了探索串置前掠翼气动特性受前掠角变化的影响,基于一种串置前掠翼身组合基本模型,保持机翼展长和几何面积不变,构建不同前掠角的流场计算模型。采用FLUENT软件数值计算纵向气动力和粘性流场随前掠角和迎角的变化特性,选择远场来流马赫数0.8,迎角0°^+40°。前掠角20°模型在迎角0°~30°呈现出高升力系数和高升阻比,最大升阻比迎角为10°。前掠角40°模型升力系数在40°迎角时达到最大且未失速,大迎角气动特性良好。前翼和后翼对模型整体升力的贡献有所差异,前掠角是串置前掠翼构型气动特性的重要影响因素,通过改变前掠角能够获得合适的布局气动力性能。

In order to explore the influence of forward swept angle on the aerodynamic characteristics of the tandem forward swept wing,the flow field calculation models of different forward swept angles were constructed with the wing’s length and geometric area unchanged,basing on a basic model of the tandem forward swept wing-fuselage combination.The varying characteristics of longitudinal aerodynamic force and viscous flow field with the forward swept angle and angle of attack were simulated numerically by FLUENT software,in which the free flow Mach number is 0.8 and the angle of attack is 0°^+40°.The 20°model of the forward swept angle exhibits a high lift coefficient and a high lift-to-drag ratio at the angle of attack of 0°~30°,and the angle of attack of maximum lift-to-drag ratio is 40°.The lift coefficient of the model with swept angle of 40°reaches the maximum at the angle of attack of 10°without stalling,and the aerodynamic characteristics of the high angle of attack is good.The contribution of the front and rear wings to the overall lift of the model is different,and the forward swept angle is an important factor affecting the aerodynamic characteristics of the tandem forward swept wing configuration.The appropriate layout aerodynamic performance can be obtained by changing the forward swept angle.