Effects of Blade Tip Sweep on the Flowfield and Aerodynamic Characteristics of Rotors
The relationship of the section normal Mach number and equivalent angle of attack between a rotor with swept tip and that with rectangular tip was derived. It was proved that the normal flow on a swept tip is not always less than that on a rectangular tip at forward flight and an azimuthal interval where the normal Mach number on a swept tip is larger than that on a rectangular tip was given. Also, the condition of the swept angle distribution to avoid this situation and a new curvilinear swept tip design to maintain a constant leading edge normal Mach number was proposed. CFD analysis was carried out to simulate the transonic flowfield of a swept tip rotor in both hover and forward flight conditions. Based on the theoretical and numerical results, the effect of blade tip swept on the rotor flowfield characteristics and performance, especially on the shock wave location and strength near the tip were studied.
ZHAO Qi-jun XU Guo-hua XU Guang
National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics Nanjing University of Aeronautics and Astronautics Nanjing, Jiangsu, 210016, China
国际会议
南京
英文
1-12
2009-10-14（万方平台首次上网日期，不代表论文的发表时间）