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.
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Document Type: Research Article
The Boeing Company, Vertol Division, Morton, Pennsylvania
Publication date: 01 October 1967
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