In order to improve the aerodynamic performance of high-speed aviation propeller, the variation of lift-drag ratio and Mach number 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.