A model for each of the basic flow elements involved in the unsteady stall of a two-dimensional airfoil in incompressible flow is presented. The interaction of these elements is analyzed using a digital computer. Computations of the loading during transient and sinusoidal pitching motions are in good qualitative agreement with measured loads. The method was used to confirm that large torsional response of helicopter blades detected in flight tests can be attributed to dynamic stall.
A method for analyzing dynamic stall of helicopter rotor blades
1972-05-01
Report
No indication
English
A method for analyzing dynamic stall of helicopter rotor blades
TIBKAT | 1972
|Helicopter Dynamic Stall Suppression Using Piezoelectric Active Fiber Composite Rotor Blades
British Library Conference Proceedings | 1998
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