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提出了一种基于厚度不变的翼型前后缘连续偏转变形规律,并以NACA0015翼型为例,实现了翼型变弯度的参数化。以柔性伸缩蒙皮支撑结构和机械结构实现了可连续光滑偏转后缘的变弯度翼型,验证了变形规律。以前后缘偏转角度为参数,计算并分析了各个变形状态下翼型扰流流场和气动特性,讨论了变形参数对气动特性的影响,研究了气动特性的产生机理。研究结果表明:在大迎角下,前缘偏转角对翼型失速有一定的抑制作用;在中小迎角范围内,翼型升阻比随着后缘偏转角的增大而增大,且不论迎角如何变化,总可以通过前后缘偏转来获得较高的升阻比。
A continuous and deflected rule of forward and backward airfoil based on constant thickness was put forward. Taking NACA0015 airfoil as an example, parameterization of airfoil camber was realized. The flexible and retractable skin support structure and mechanical structure were used to realize the variable-curvature airfoil which can continuously and smoothly deflect the trailing edge. The deformation law was verified. Based on the deflection angles of the front and rear edges, the flow field and aerodynamic characteristics of the airfoil spoiler are calculated and analyzed. The influence of the deformation parameters on the aerodynamic characteristics is discussed and the generation mechanism of the aerodynamic characteristics is also studied. The results show that, at high angle of attack, the deflection angle of the leading edge has a certain inhibition effect on the airfoil stall. In the middle and small angle of attack range, the lift-drag ratio of the airfoil increases with the increase of the trailing edge deflection angle Regardless of how the angle of attack changes, always by the front and rear edge deflection to get a higher lift-drag ratio.