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Dynamic Stall Considerations in Helicopter Rotors

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An experimental investigation was conducted of the effect of pitching rate and pitching axis location on the aerodynamic loading of a two‐dimensional airfoil during non‐oscillatory pitching motion to a large angle of attack. The paper presents and interprets selected test results which are believed to be applicable to a helicopter blade experiencing dynamic stall. Rate of change of angle of attack is established as the dominant factor determining the very large peak lift and moment acting on the airfoil during the stall process. Pitching axis location has little effect on the peak loading, but substantial effect on the angle of attack at which dynamic stall occurs, suggesting that the loading is relatively independent of the dynamic stall angle.
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Document Type: Research Article

Affiliations: Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, Massachusetts

Publication date: 1968-04-01

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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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