排式充气机翼的高效气动布局研究

为了提高充气机翼的刚度特性,需要采用较大厚度的翼型,但厚翼型气动效率整体上又不太高。探讨一种适用于低速充气类飞行器的排式双翼布局方案,并尝试给予后翼一定的初始安装偏转角,同时还研究了双翼相对位置以及翼型特性对该排式双翼布局方案的影响。数值模拟结果表明,后翼前缘驻点附近的高压区增大了前翼下表面的压力,使此种布局较普通单翼布局在中小迎角范围内可以明显提高飞行器的升力和升阻比,其中迎角4°时可将升阻比提高62.8%,而给后翼2°的偏转角可使将升阻比提高幅度达到70.5%。同时,双翼相对位置对飞行器气动性能的影响较为敏感。此外,翼型厚度越大,弯度越小,所提出的排式双翼布局方案提高升阻比的效果越明显。综合效果来看,文中探讨的布局可为充气飞机的设计提供一个新思路。

Research on effective aerodynamic configuration of row inflatable wings

Airfoils of larger thickness are needed to improve the rigidity of the inflatable wing,while their aerodynamic efficiency is generally not great.A new aerodynamic configuration of double row wings applied to low-speed aircraft is discussed in this paper,and based on this,a new configuration which adds proper installation angle to the posterior wing is discussed.Moreover,the effect of the relative location of the double wings as well as the airfoil thickness on the row double-wing configuration is also studied.Numerical simulation result indicates that high-pressure zone around stagnation point at the leading edge of the posterior wing increases the pressure under the anterior wing,which will improve the lift and lift-drag ratio of aircraft obviously at a range of small and middle angles of attack.At a 4° angle of attack,the lift-drag ratio is improved by an extent of 62.8%,while 2° installation angle to the posterior wing is able to further improves the lift-drag ratio of the wing-body by 70.5%.Meanwhile,aerodynamic performance of the double-wing configuration is sensitive to the relative location of the double wings.The thicker is the airfoil,the smaller is the camber,and the more efficient is the row wing configuration studied.The overall effect shows that the aerodynamic configuration researched provides a new approach to the design of inflatable aircrafts.