Full-scale wind-tunnel test of the aeroelastic stability of a bearingless main rotorThe rotor studied in the wind tunnel had previously been flight tested on a BO-105 helicopter. The investigation was conducted to determine the rotor's aeroelastic stability characteristics in hover and at airspeeds up to 143 knots. These characteristics are compared with those obtained from whirl-tower and flight tests and predictions from a digital computer simulation. It was found that the rotor was stable for all conditions tested. At constant tip speed, shaft angle, and airspeed, stability increases with blade collective pitch setting. No significant change in system damping occurred that was attributable to frequency coalescence between the rotor inplane regressing mode and the support modes. Stability levels determined in the wind tunnel were of the same magnitude and yielded the same trends as data obtained from whirl-tower and flight tests.
Document ID
19810062216
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Warmbrodt, W. (NASA Ames Research Center Moffett Field, CA, United States)
Mccloud, J., III (NASA Ames Research Center Moffett Field, CA, United States)
Sheffler, M. (NASA Ames Research Center Moffett Field, CA, United States)
Staley, J. (Boeing Vertol Co. Philadelphia, PA, United States)