Amplitude effects on dynamic stall of an oscillating airfoil
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Amplitude effects on dynamic stall of an oscillating airfoil in locally transonic flow were studied using stroboscopic schlieren flow visualization. The dynamic stall vortex was photographed for various conditions and its properties were documented. Results show a pronounced effect of the amplitude of oscillation. The airfoil flow can sustain the larger amplitudes with the vortex retained on the surface and thus, produce dynamic lift to higher angles of attack at higher amplitudes. A possible explanation for this is offered in terms of the vorticity generation due to surface acceleration and local streamwise pressure gradient. Also, for the first time a shock has been photographed on the airfoil upper surface and some of its characteristics are discussed.
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Sahin, Mehmet; Sankar, Lakshmi N.; Chandrasekhara, M.S.; Tung, Chee (American Institute of Aeronautics and Astronautics Inc., 2000);Dynamic stall calculations were carried out for an airfoil with a deformed leading edge shape at a freestream Mach number of 0.3. The surface deformations were done about a baseline NACA 0012 airfoil, effectively ...
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, ...
Chandrasekhara, M.S.; Carr, L.W.; Wilder, M.C. ;The compressible dynamic stall flowfield over a NACA 0012 airfoil transiently pitching from 0 to 60 deg at a constant rate under compressible flow conditions has been studied using real-time interferometry. A quantitati ...