MODEL TILT-ROTOR HOVER PERFORMANCE AND SURFACE PRESSURE MEASUREMENT

A test of a small scale 3-bladed model rotor, with geometry typical of that used on tilt-rotor aircraft, was conducted in the Army Aeroflightdynamics Directorate’s anechoic hover chamber. The purpose of this test was to determine the hover performance of the rotor and investigate the pressure distributions on a blade at various collective pitch angles and tip speeds. The measured pressures indicate that the rotor did not stall for high collective pitch angles up to θc = 25°. This is clearly a three dimensional effect since two-dimensional theory predicts flow separation at these high angles. The flow near the trailing edge separated above θc = 25° which caused a sharp increase in power.