An improved propeller design method for the electric aircraft

Abstract In this paper, an improved propeller design method for the electric aircraft was presented. For a given operative condition and profile distribution along the blade, the present method can determine the chord and pitch angle distribution of the blade, together with its efficiency and its torque and thrust coefficients of the maximum efficiency propeller. According to the flight velocity, thrust and rotate speed of cruise condition, the propeller of an electric aircraft was designed using the present method. Wind tunnel test of scaled model of propeller (diameter 0.96 m) was carried out. The test results show that present method was suitable to design the propeller of the electric aircraft.