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A Lifting Line Theory for Curved Helicopter Blades in Hovering and Axial Flight

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A lifting line model to calculate the aerodynamic loads along a curved helicopter blade, in hovering and axial flight, is derived. In the derivation a “semi‐rigid” wake model, which depends on the induced velocity distribution along the blade, is used. The influence of both trailing and bound vortices is taken into account. The derivation yields an efficient numerical scheme of calculations. Results for two different curved blades are presented and compared with similar straight blades. It is shown that curvature influences the distribution of the aerodynamic properties along the blades. Good agreement between the results of the present lifting line theory and a “momentum‐blade element” theory for curved blades is also presented.

Document Type: Research Article


Affiliations: Department of Aeronautical Engineering, Technicon—Israel Institute of Technology, Haifa, Israel

Publication date: 1984-07-01

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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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