Amplitude effects on dynamic stall of an oscillating airfoil

Abstract

y d g e s ' Navy -N A S A Joint I n s t i t u t r of Aeronautics Department of Aeronautics a n d Astronautics Naval P o s t g r a d u a t e School, Monterey, CA a n d Fluid Mechanics I.aborat,ory, Fluid Dynamics Research Blanch NASA Ames R.esearcli Center M o f f r t t Field, CA Abstract 1. Introdirctiorr

Laser velocimetry measurements of oscillating airfoil dynamic stall flow field

“…0O tb.t back side, however, the flow is same as the local boundary layer as at this location, it very turbulent ann thils, only a few density contours is about 4-5% chord thick depending upon the angle could be seen The L V data of Chandrasekhara and of attack. Thus, a few measurement points could be VanD:,ken 13 shoi:s th-t the velocities rise when the obtained. At larger phase angles, at this location, the bubble breaks at aroi nd 4 -2000 , indicating a fair effect of the dynamic stall vortex is felt strongly.…”