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The Influence of Blade Flapping Restraint on the Dynamic Stability of Low Disk Loading Propeller‐Rotors

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The dynamic stability of low disk loading propeller‐rotors is examined as a function of the various dimensionless parameters characterizing the design. It is found that a definite design optimum exists for typical systems and is obtained by appropriate tuning of the blade fundamental flapping frequency ratio. This optimum tuning is approximately 1.1 to 1.2 cycles per revolution and is insensitive to the other dimensionless parameters such as nacelle equivalent viscous damping ratios, nacelle pivot distance ratio and rotor blade element mean angle of attack. It is shown that at this design optimum the static and dynamic stability design requirements coalesce, and that a greatly simplified design analysis is possible in terms of a static divergence criterion which is derived.

Document Type: Research Article


Affiliations: The Boeing Company, Vertol Division, Morton, Pennsylvania

Publication date: October 1, 1967

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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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