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