“钻石背”弹翼气动特性数值模拟研究

用计算流体力学与阻力系数工程预估相结合的方法研究了"钻石背"弹翼前、后翼条之间气动干扰以及翼型、前后翼条的相对高度对气动特性的影响。计算结果与实验结果对比表明,在中小攻角,数值计算与阻力系数工程预估相结合的方法是可信的;采用亚声速低阻NACA64-108翼型可明显地增大"钻石背"弹翼的升力,减小阻力,增大升阻比;钻石背"弹翼前、后翼条之间的气动干扰,使升力减小,阻力增大;前翼条在上,后翼条在下的配置能减弱这种不利的气动干扰,并且在计算的范围内,后翼条至前翼条的垂直位置ΔH为9mm时,"钻石背"弹翼前、后翼条之间的气动干扰最小,升阻比最大。

Numerical Simulation for Aerodynamic Characteristics of Diamondback Wing

Computational fluid dynamics and semi-empiric method were used to study the effect of Diamondback wing geometric parameters on its aerodynamic characteristics. The comparison of calculation and experiment results indicate that this method is accurate for the small and medium angle of attack. The aerofoil NACA64-108 can obviously increase the lift and lift-drag ratio of Diamondback wing. The aerodynamic interference between the front-wing-strip and rear-wing-strip will reduce the lift and increase the drag. The configuration that the front-wing-strip is higher than the rear-wing-strip can reduce the interference between two strips. If the height difference between two strips is 9 mm, the aerodynamic interference is minimum, and the lift-drag ratio reaches maximum.