A full-scale XH-59A advancing blade concept helicopter was tested in Ames Research Center's 40 by 80 foot wind tunnel. The helicopter was tested with the rotor on and off, rotor hub fairings on and off, interrotor shaft fairing on and off, rotor instrumentation module on and off, and auxiliary propulsion thrust on and off. An advance ratio range of 0.25 and 0.45 with the rotor on and from 60 to 180 knots with the rotor off was investigated. Data on aerodynamic forces and moments, rotor loads, rotor control positions and vibration for the XH-59A as well as the aerodynamic performance of the isolated rotor are presented.
Performance and loads data from a wind tunnel test of a full-scale, coaxial, hingeless rotor helicopter
1981-10-01
Report
Keine Angabe
Englisch
Full-scale hingeless rotor performance and loads
NTRS | 1995
|Correlation of Wind Tunnel and Flight Test Results of a Full-Scale Hingeless Rotor
British Library Conference Proceedings | 1993
|