Performance and Pressure Data from a Small Model Tilt-Rotor in Hover.
AVIATION AND TROOP COMMAND (ARMY) ST LOUIS MO
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A test of a small three-bladed model rotor, with geometry typical of that used on tilt-rotor aircraft, was conducted in the U.S. Army Aeroflightdynamics Directorates anechoic hover chamber. The objectives of the test were to determine the hover performance of the rotor and investigate the pressure distributions on a blade operating at various collective pitch angles and tip speeds. This report presents the rotor performance data and blade surface pressures.