Keywords: Rotary wing, Aeroelastic stability, Wind tunnel test
Abstract: A full-scale BO-105 hingeless rotor system was tested in the Ames 40- by 80-Foot Wind Tunnel on the rotor test apparatus. Rotor performance, blade and rotor hub loads, and aeroelastic stability as functions of rotor lift, tunnel velocity, and shaft angle were investigated. The primary objective of this test program was to create a data base for full-scale hingeless rotor performance, structural blade loads, and aeroelastic stability. A secondary objective was to investigate the ability to match flight test conditions in the wind tunnel. This data base can be used for the experimental and analytical studies of hingeless rotor systems over large variations in rotor thrust and tunnel velocity. Aeroelastic stability data and the corresponding rotor performance data and test conditions for tunnel velocities from hover to 140 knots and thrust coefficients (CT/Sigma) from 0.0 to 0.10 are presented in this report. The rotor was found to be stable at all conditions tested.
NASA Ames Research Center, Moffett Field CA 94035-1000, (650) 604-5000
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