Experimental investigation was conducted of effect of pitching rate and pitching axis location on aerodynamic loading of two-dimensional airfoil during nonoscillatory pitching motion to large angle of attack; selected test results, believed to be applicable to helicopter blade experiencing dynamic stall, are presented; rate of change of angle of attack is established as dominant factor determining very large peak lift and moment acting on airfoil during stall process.
Dynamic stall considerations in helicopter rotors
Am Helicopter Soc -- J
American Helicopter Society -- Journal ; 13 , n 2
1968
7 pages
Article (Journal)
English
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Dynamic Stall Considerations in Helicopter Rotors
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