Computational Modelling of Unsteady Airfoil Flows
Results
Two different cases have been investigated: a light-stall case at lower angle of attack [ alpha=11+4.2 sin(wt) ] and a deep-stall case at high angle of attack [ alpha=15+4.2 sin(wt) ].
Light-stall case
Deep-stall case
Background
Dynamic Stall
Comp. Approach
Results
Animations
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Last modified: Thu Feb 10 10:29:13 CET 2000
Results 
