Abstract
Abstract : Surface pressure measurements were taken in an experimental investigation of energetic dynamic stall vortices. The associated unsteady flowfield was generated by a 6-in. NACA 0015 airfoil pitching at high rates to large angles of attack. The airfoil pitch rates varied from 230 deg/sec to 1380 deg/sec and angles of attack varied from zero degrees to 60 degrees. Pitching occurred about its quarter-chord axis. Pitch rate, Reynolds number, and the non- dimensional pitch rate, alpha plus, were varied to determine the effects on pressure and lift coefficients. It was found that increases in pitch rate and Reynolds number has inverse effects on the flowfield in the immediate vicinity of the airfoil. Maintenance of a constant non-dimensional pitch rate produced very similar flowfields and pressure coefficients.
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