| Citation: | WANG Tianjian, HAN Dong, CUI Zhao. Perforated Gurney flaps to improve hovering performance of helicopter rotors[J]. Journal of Aerospace Power, 2026, 41（1）：20240268 doi: 10.13224/j.cnki.jasp.20240268
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A study was conducted for the improvement of hovering performance by perforated gurney flaps’ application on helicopter rotor. First, the aerodynamic characteristics of perforated gurney flaps were discussed using computational fluid dynamics (CFD) method, and then an aerodynamic model of flapped airfoil was established. The performance improvement of the helicopter rotor equipped with perforated gurney flaps was analyzed by the coupling of a helicopter flight performance analysis model with the perforated gurney flap aerodynamic model. The results indicated that the jets brought by the holes interruptted the trailing-edge vortex shedding, thereby reducing the drag and increasing the lift to drag ratio. The analysis of hovering performance showed that after the installation of gurney flaps, at the cost of slightly sacrificing performance under low loads, a significant increment of figure of merit and reduction of power required under high loads was achieved. Also a reduction of angle of attack of rotor blade was convinced, thus the blade load distribution was improved. The afore mentioned effects of perforated gurney flaps increased significantly with the outward expansion of installation position. A 2% chord height, 23% porosity perforated gurney flap equipped at the radial 80% to 95% radius of the rotor blade can increase figure of merit by 10.60% and reduce power required by 10.00% under high loads, thus the maximum thrust of the rotor increased by 5.17% and the corresponding figure of merit increased by 7.82%.
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