基于数值模拟方法的机翼上反角研究与设计

Design and Study on Dihedral Angles Based on Numerical Simulation

针对某大展弦比、上单翼、低速飞机,利用数值模拟技术,对其机翼上反角的空气动力特性进行研究。数值模拟结果表明:机翼上反角对该类飞机升阻特性及俯仰力矩特性影响较小,上反使升力略有损失;对横航向空气动力特性影响较大,尤其是对横向静稳定性影响较为显著,上反角每增加1°横向静稳定性Clβ约增加18.7%,而下反角则降低了横向静稳定性;对航向静稳定性略有影响,上反角使Cnβ略有降低,下反角使Cnβ稍有增加。以上结论可作为同类飞机初步设计或改进改型时的参考和依据。

In view of the low-speed aircraft of high aspect ratio and high wing,it studies on aerodynamics characteristics of wing dihedral angles based on numerical simulation technique. The simulation results show that the effect of wing dihedral angles on lift,and drag and pitch moment is weak. Lift has been slightly decreased as the result of dihedral angles. The effect on lateral and directional aerodynamics characteristics is large,especially on lateral stability. When the dihedral angle of wing is increasing 1°,lateral stability is increased by 18.7%. Oppositely,lateral stability has been decreased as negative dihedral.Directional stability has been slightly decreased as positive dihedral,and slightly increased as negative dihedral. The conclusion given above can supply references to conceptual design or remodel for the same kind of aircraft.