低桨尖速度旋翼加装格尼襟翼气动性能数值分析OA

To explore the potential for increasing lift on low tip-speed rotors,a rotor performance calculation model is established.The flight data of the UH-60A helicopter are utilized to validate this model.Further research is conducted on the influence of the Gurney flap on the hovering and forward flight performance of the low tip-speed rotor.The results indicate that,in hover,Gurney flaps increase rotor thrust but with higher power consumption.The thrust coefficient rises by up to 12.00%,while the power coefficient increases by 7.98%.Under high-thrust conditions,Gurney flaps enable the rotor to maintain the same thrust as the baseline configuration at a reduced collective pitch,thereby significantly improving the figure of merit by 18.55%.In forward flight(100 km/h),the thrust coefficient improves by 11.30%,but with greater power penalty(power coefficient increases by 18.64%).Gurney flaps also improve the lift-to-drag ratio,with a maximum increase of 28.77%.For low tip-speed rotors,at a given thrust,Gurney flaps reduce the angle of attack and increase the lift-to-drag ratio,thereby improving rotor aerodynamic performance in high-thrust conditions.