Flap‐Lag‐Torsion Aeroelastic Stability of Circulation‐Controlled Rotors in Hover

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Abstract
The results of a theoretical investigation of the flap‐lag‐torsion stability of circulation‐controlled rotors in hover are presented. Stability boundaries are presented as a function of thrust and lag frequency, at several levels of blowing coefficient, for flap frequencies of 1.1/rev and 1.8/rev. The effects of several parameters on the blade flap‐lag stability are examined, including structural damping, structural coupling, pitch‐lag and pitch‐flap coupling, and the blade feathering mothion. The trailing edge blowing can have a major impact on the blade aeroelastic stability, which should be considered in the rotor design. The implications of there results for the current CCR and X‐Wing rotorcraft designs are considered.

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