Wing tunnel test data on a 1/4.622 Froude scale, hingeless rotor, tilt rotor mode are reported for all potential flight conditions through hover and a wide envelope of transitions. A mathematical model was used to describe the rotor system in real time simulation by means of regression analyses. Details of the model, test program and data system are provided together with four data files for hover and transition. Diverse data are presented; variables include parametric force, moment and blade fatigue loads, flight range, airspeed, aircraft attitude, rotor control inputs, wing flap deflection, thrust loads and rotor RPM.
Wind Tunnel Test on a 1/4.622 Froude Scale, Hingeless Rotor, Tilt Rotor Model, Volume 1
1976
779 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Rigid rotors , Tilt rotor research aircraft program , Scale models , Wind tunnel tests , Aerodynamic loads , Froude number , Hovering , Low speed , Mathematical models , Nasa programs , Regression analysis , Tables (Data) , Aerodynamic forces , Airspeed , Attitude (Inclination) , Flight characteristics , Rotor speed , Stability derivatives , Stress concentration , Thrust loads , Wing flaps , Rotor blades(Rotary wings)