An experimental and analytical study was conducted to determine the effects of blade structural design parameters on the stall-related operating boundaries of helicopter main rotors. Emphasis was placed on the effects of blade torsional properties on the buildup of vibratory control loads in stall. The analytical methods used in the study were evaluated through correlation with data for two full-scale rotors and data obtained on a two-dimensional airfoil system whose torsional dynamics simulated those of a rotor blade. (Modified author abstract)
Investigation of the Effects of Blade Structural Design Parameters on Helicopter Stall Boundaries
1974
157 pages
Report
Keine Angabe
Englisch
Active Control of Helicopter Blade Stall
Online Contents | 1998
|Active Control of Helicopter Blade Stall
NTRS | 1996
|Active control of helicopter blade stall
AIAA | 1996
|Active Control of Helicopter Blade Stall
AIAA | 1998
|