加装格尼襟翼的自转旋翼气动特性研究

Abstract

Abstract: In order to investigate the aerodynamic characteristics of auto-rotating rotors equipped with Gurney flaps, a numerical model of airfoils equipped with Gurney flaps is established. The aerodynamic characteristics of airfoil NACA0012 with Gurney flaps of the height of 1% and 2% of chord are calculated respectively. The validity of the model is also provided by the test data. The aerodynamic model of auto-rotating rotors is established based on the blade element theory, with a Pitt-Peters dynamic inflow model to capture the non-uniform induced velocity distribution on the rotor disk. The aerodynamic characteristics of auto-rotating rotors equipped with Gurney flaps with different heights are analyzed. The results show that from 20 m/s to 35 m/s forward flight velocity, the average drag reduction of auto-rotating rotors is up to 26% with the 1% chord height Gurney flap, and the average drag reduction of auto-rotating rotor is up to 17% with the 2% chord height Gurney flap. Thus, the aerodynamic efficiency of the autogiro rotor is improved significantly with Gurney flaps.

Key words: Gurney flap, auto-rotating rotor, blade element theory, aerodynamic characteristic, lift drag ratio

CLC Number:

V211.52

CUI Zhao, HAN Dong, LI Jianbo, JI Leqiang, ZHU Qinghua. Study on Aerodynamic Characteristics of Auto-rotating Rotors with Gurney Flaps[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(10): 1791-1799.

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Study on Aerodynamic Characteristics of Auto-rotating Rotors with Gurney Flaps

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