Analysis of Pitch and Plunge Effects on Unsteady Airfoil Behavior
Abstract:An analysis was conducted into the effects of pitch versus plunge forcing an unsteady airfoil behavior. Experimental measurements of unsteady airloads were analyzed in conjunction with classical unsteady airfoil theory and a semi‐empirical model for dynamic stall. The separate contributions to the unsteady airloads due to angle of attack and pitch rate are shown to be the key variables governing aerodynamic damping, the onset of leading edge separation, and dynamic stall.
Document Type: Research Article
Affiliations: Ctr. for Rotorcraft Education and Research, Dept. of Aerospace Engineering, University of Maryland, College Park, Md.
Publication date: July 1, 1992
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