Wind Tunnel Test of the Conversion Process of a Folding Tilt Rotor Aircraft Using a Semispan Unpowered Model. Volume 4. Part 1. Analysis and Results
BOEING VERTOL CO PHILADELPHIA PA
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Wind tunnel test data obtained with a 33.75-inch diameter nonarticulated folding tilt rotor mounted on a semispan wing show the effects of collective pitch schedule variations on transient lift, drag, and pitching moment of the aircraft. Blade loads data presented show that loads do not limit the conversion process. The model was configured with proprotor blades which had an in-plane natural frequency of less than 1.0rev. The testing included study of the aerodynamics and dynamics of rotor spin-up, spin-down, stopping, and steady windmilling. Correlation with predictions of transient aerodynamic performance static derivatives of the proprotor, and blade loads are included.