Experimental Study for Aerodynamic Performance of Quadrotor Helicopter

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  • NGUYEN Duc Hung
    Department of Aerospace Engineering, Nagoya University
  • LIU Yu
    Department of Aerospace Engineering, Nagoya University
  • MORI Koichi
    Department of Aerospace Engineering, Nagoya University

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Description

Wind tunnel experiments are performed to investigate the aerodynamic characteristics of a quadrotor helicopter in a uniform flow. At first, the thrust and drag coefficients of a single rotor under low-Reynolds number conditions are measured to deduce the basic design parameters of the rotor. Second, the aerodynamic interference between two rotors in a tandem configuration is investigated. It is experimentally found that the thrust coefficient of the rear rotor is a maximum of 11% lower than that of the front rotor during forward flight. Moreover, it is found that the interference effect of the front rotor on the rear rotor can be predicted qualitatively using a theoretical formula on the basis of the Biot-Savart Law. Finally, it is shown that the theoretical predictions of the thrust coefficient and drag coefficient agree well with the experimental results of a quadrotor helicopter model within limited ranges of the inflow ratio and advance ratio.

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