Simulations of a plunging airfoil at Re=60,000 find that 2D leading-edge actuation in a certain frequency band disrupts the stall vortex, raising suction-side pressure near the trailing edge to reduce drag while preserving lift.
Carr, Progress in analysis and prediction of dynamic stall, Journal of Aircraft 25, 6 (1988)
1 Pith paper cite this work. Polarity classification is still indexing.
1
Pith paper citing it
fields
physics.flu-dyn 1years
2019 1verdicts
UNVERDICTED 1representative citing papers
citing papers explorer
-
Active Flow Control for Drag Reduction of a Plunging Airfoil under Deep Dynamic Stall
Simulations of a plunging airfoil at Re=60,000 find that 2D leading-edge actuation in a certain frequency band disrupts the stall vortex, raising suction-side pressure near the trailing edge to reduce drag while preserving lift.