高速航空螺旋桨翼型气动特性及数值仿真

Numerical Simulation on Aerodynamic Performance of Airfoils Using byHigh Speed Aviation Propeller

为了提升高速航空螺旋桨的气动性能,通过计算流体力学(computational fluid dynamics,CFD)方法研究了平凸翼型NACA4412、超临界翼型RAE2822和高雷诺数薄翼型NACA65206在不同马赫数Ma、不同攻角下的升阻比变化规律,以及翼型流场的马赫数等值线分布等。通过翼型的升阻比特性研究,选用NACA65206翼型设计了一款高速航空螺旋桨,并进行了螺旋桨流场的CFD仿真和气动性能计算。结果表明:随着马赫数从0.5提高到0.9,NACA65206翼型具有更好的升阻比特性,并且失速特性不断改善;采用NACA65206翼型设计的螺旋桨在0.6飞行马赫数下,推进效率高于80%,在0.7飞行马赫数下,推进效率高于75%,说明了使用薄翼型结合大后掠角度设计的高速航空螺旋桨具有较好的推进效率。

In order to improve the aerodynamic performance of high-speed aviation propeller,the variation of lift-drag ratio and Mach number Ma contour distribution of flat convex airfoil NACA4412,supercritical airfoil RAE2822 and high Reynolds number thin airfoil NACA65206 under different Mach numbers and different attack angles were studied by computational fluid dynamics method(CFD).Through the study of the lift-drag ratio characteristics of the airfoils,the NACA65206 airfoil was selected to design the high-speed aviation propeller,and the CFD simulation of the flow field and aerodynamic performance calculation of the propeller were carried out.The results show that with the increase of Mach number from 0.5 to 0.9,NACA65206 airfoil has better lift drag ratio characteristics and better stalling characteristics;The propulsion efficiency of the propeller designed with NACA65206 airfoil is higher than 80%at 0.6 Mach number and 75%at 0.7 Mach number.The high-speed aviation propeller with thin airfoil and large swept angle has better propulsion efficiency.