Helicopters experience considerable areas of stall over rotor disk during high-speed and maneuvering flight; serious increases in blade control link and torsional stresses are sufficiently severe to reduce fatigue life of rotor mechanical components; general theory is developed representing dynamic stall process by shedding of vorticity from vicinity of airfoil leading edge; theory is applied to prediction of stall-induced airloading on airfoil experiencing sudden onset of flow and on airfoil performing oscillatory pitching motion; satisfactory agreement between theoretical and experimental pressure distributions, forces and moments, and vortex trajectories is shown. (06653)
Aerodynamic loading on two-dimensional airfoil during dynamic stall
AIAA J
AIAA Journal ; 6 , n 10
1968
8 pages
Aufsatz (Zeitschrift)
Englisch
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