Compressible Dynamic Stall Control Using a Shape Adaptive Airfoil
Abstract
Compressible dynamic stall control using a dynamically
deforming leading edge airfoil is reported. The
technique uses real-time leading edge shape adaptation
to manipulate the local adverse pressure gradient over
an oscillating airfoil. This produces attached leading
edge flow at all angles of attack in the cycle. The shape
change schedule is tailored to achieve the “right” airfoil
shape through the dynamic stall regime by rounding the
nose on the upstroke and sharpening it on the
downstroke. The method exploits the favorable effects
of shape adaptation on the potential flow to modify the
pressure field and maintain the peak vorticity level
below the critical level at which the dynamic stall
vortex develops. The sensitivity of the flow to rate of
nose curvature change and the angle of attack at which
the initiation occurs has been investigated.
Description
AIAA Paper 99-0650 Reno, NV, Jan. 1999 (Under Review for AIAA Journal).
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