Reattachment Studies of an Oscillating Airfoil Dynamic Stall Flow Field
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The reattaching flow over an oscillating airfoil executing large amplitude sinusoidal motion around a mean angle of attack of 10 degrees has been studied using the techniques of stroboscopic schlieren, two component laser Doppler velocimetry and point diffraction interferometry, for a free stream Mach number of 0.3 and a reduced frequency of 0.05. The results show that the dynamically stalled flow reattaches in a process that begins when the airfoil is very close to the static stall angle on its downward stroke and progresses over the airfoil through a large range of angles of attack as the airfoil angle decreases to about 6 degrees. The airfoil suction peak shows a dramatic rise as the static stall angle is approached and the velocity profiles develop such that the flow near the surface is accelerated. The process completes through the disappearance of a separation bubble that forms over the airfoil.
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Chandrasekhara, M.S.; M.C.Wilder; L.W.Carr (1997);A novel way of controlling compressible flow separation, using a dynamically deforming leading edge airfoil whose nose curvature can be changed by 400% to keep the flow attached at post-stall angles of attack is reported. ...
Ahmed, S.; Chandrasekhara, M.S ;The reattaching flow over an oscillating airfoil executing large-amplitude sinusoidal motion around a mean angle of attack of 10 deg has been studied using the techniques of stroboscopic schlieren, two-component laser Doppler ...
Sahin, M.; Sankar, N.L.; Chandrasekhara, M.S; Tung, C. ;Dynamic stall calculations were carried out for an airfoil with a dynamically deformed leading-edge (DDLE) shape at a freestream Mach number of 0.3. The surface deformations were done about a baseline NACA 0012 airfoil, ...