Abstract: In order to study the propulsion plant of high-speed helicopter, the aerodynamic optimization design and the aerodynamic performance calculation of tail-thrust propeller of high-speed helicopter have been investigated based on the theory of propeller standard strip analysis and the theory of the vortex optimization design theory of screw propellers. During the design process, taking the high speed flight condition of H=2 000 m, v=400 km/h as the design point, a propeller aerodynamic shape with diameter of 2.5 m was determined, including the distribution of optimal circulant, chord length and angle of twist were given. Based on the strip theory, the aerodynamic performance of the propeller under different working conditions was calculated. The results show that the propeller can maintain high efficiency（η=0.80-0.85） in wide advance ratio range. The aerodynamic performance under static condition with v=0 km/h and high speed condition with v=400 km/h are calculated by CFD numerical simulation method. The aerodynamic performance parameters and flow field information of propeller are obtained. The difference of tension coefficient and efficiency between the numerical calculation and theoretical calculation is 1%-2%.Therefore, the reliability of aerodynamic design of high-speed helicopter tail-thrust propeller is verified.