An investigation of the effect of moderate sweep on three-dimensional (3D) dynamic stall of a pitching finite-aspect-ratio wing is performed by means of large-eddy simulations. The wings have an aspect ratio and a NACA 0012 section. Three values of sweep angle are considered, , and 30°. The flow parameters are freestream Mach number and chord Reynolds numbers . A sinusoidal pitching motion is considered with reduced frequency and minimum and maximum angles of attack of 4° and 22°. The unsteady flow structure is examined in order to provide a model of 3D dynamic stall over finite swept wings. For all configurations, the dynamic stall vortex evolves into an arch-type structure that is shed following its transformation into a ring vortex. For , there is a single and larger arch vortex centered about midspan. For the swept cases, arch vortices are formed on each side of the wing at a spanwise station that moves farther outboard with increasing sweep. For , the outer leg of the arch vortex interacts strongly with the wing tip flow and abrupt tip stall is observed.
Effect of Sweep on Dynamic Stall of a Pitching Finite-Aspect-Ratio Wing
AIAA Journal ; 57 , 8 ; 3274-3289
2019-08-01
Conference paper , Article (Journal)
Electronic Resource
English
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