PIV Invastigation of UAV Rotor in Hover

This paper presents the results of an experimental study of the aerodynamic performance of a helicopter rotor for UAV applications in steady hover at Reynolds numbers below 50 000 by means of particles image velocimetry (PIV). Results are shown for a two-bladed rotor configuration for various pitch angles and angular velocities. A brief description of the designed test stand and PIV system is provided. The experimental setup allows for the measurement of thrust, torque and velocity field around the helicopter rotor with diameters of up to 1 meter, for pitch angles varying from −12° to +24° and for angular velocities of up to 3 000 RPM. The internal friction losses of the test stand are estimated and taken into account in measurements. Conclusions are drawn about the aerodynamic performance of the studied rotor configuration.