Naval Postgraduate School
Compressible Dynamic Stall Vorticity Flux Control Using a Dynamic Camber Airfoil
Chandrasekhara_Compressible_2007.pdf (571.7Kb)Metadata
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This study reports control of compressible dynamic stall through
management of its unsteady vorticity using a variable droop leading edge (VDLE)
airfoil. Through dynamic adaptation of the airfoil edge incidence, the formation
of a dynamic stall vortex was virtually eliminated for Mach numbers of up to 0·4.
Consequently, the leading edge vorticity flux was redistributed enabling retention
of the dynamic lift. Of even greater importance was the fact that the drag and
pitching moment coefficients were reduced by nearly 50%. The camber variations
introduced when the leading edge was drooped are explained to be the source of
this benefit. Analysis of the peak vorticity flux levels allowed the determination of
minimum necessary airfoil adaptation schedule.
Description
Invited Paper Sadhana; Journal of Indian Academy of Sciences, Vol. 32, Part 1 & 2, February-April 2007, pp. 1-10.
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