Unsteady Stall Control Using Dynamically Deforming Airfoils
Author
Chandrasekhara, M.S.
Wilder, M.C.
Carr, L.W.
Metadata
Show full item recordAbstract
An experiment documenting the compressible flow over a dynamically deforming airfoil is presented. This airfoil,
which has a leading-edge radius that can be dynamically changed, was tested at various deformation rates for fixed
airfoil angle of attack. Selected leading-edge shapes were also tested during airfoil oscillation. These tests show
that for a range of Mach numbers observed on the retreating blades of helicopter rotors the dynamic stall vortex
can be avoided by a judicious variation of leading-edge curvature.
Description
The article of record as published may be found at http://dx.doi.org/10.2514/2.294