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基于扇翼飞行器翼型特殊的几何形状及流场特性,在原有翼型的弧形槽下方和后缘加装控制阀门,通过调节阀门开启及开启尺寸的大小,利用弧形槽低压涡所产生的吸力对翼型后缘的附面层进行一定的控制,达到增升减阻的效果。通过采用计算流体力学的方法对其机理及阀门开启尺寸的影响进行了详细计算和分析,研究表明当阀门开启的尺寸为10mm时,修改翼型的最大升力系数、失速迎角及相同迎角下的升力系数和推力系数均大于基本翼型;随着阀门开启尺寸的增大,修改翼型的最大升力系数和失速迎角均减小,但是在失速前,修改翼型在相同迎角下的升力系数大于基本翼型。此方法可以改变先前通过增大横流风扇的转速来提高其气动性能的做法,减小了能量的消耗,增大了整个飞行器的航程,为扇翼飞行器能够早日投入实际运用奠定了一定的理论基础。
Based on the special geometry and flow field characteristics of the airfoil, the control valve is installed below and behind the arc slot of the original airfoil. By adjusting the size of the valve opening and opening, Suction on the airfoil trailing edge of the surface layer of a certain degree of control to achieve the effect of increasing drag reduction. Through the use of Computational Fluid Dynamics (CFD) method to calculate and analyze the mechanism and the effect of valve opening size, the results show that when the size of valve opening is 10mm, the maximum lift coefficient, the angle of attack at attack and the angle of attack The lift coefficient and thrust coefficient are both larger than the basic airfoil. As the valve opening size increases, the maximum lift coefficient and the angle of attack of the modified airfoil decrease, but before the stall, the airfoil at the same angle of attack Lift coefficient greater than the basic airfoil. This method can change the previous method of increasing the aerodynamic performance by increasing the rotating speed of the cross-flow fan, reducing the energy consumption and increasing the voyage of the entire aircraft, which lays a theoretical foundation for the early application of the fan-shaped aircraft in practical applications .