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Analysis of Pitch and Plunge Effects on Unsteady Airfoil Behavior

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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.
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Document Type: Research Article

Affiliations: Ctr. for Rotorcraft Education and Research, Dept. of Aerospace Engineering, University of Maryland, College Park, Md.

Publication date: 1992-07-01

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  • The Journal of the American Helicopter Society is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by AHS International and presents innovative papers covering the state-of-the-art in all disciplines of rotorcraft design, research and development. (Please note that AHS members receive significant discounts on articles and subscriptions.)

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