A mathematical model is presented for analyzing the effect of aeroelastic detuning on unstalled supersonic flutter, where the detuning mechanism employed is alternate-blade structural detuning. Two alternative aerodynamic detuning methods are compared: the novel, alternate-chordwise airfoil spacing method, and the alternate circumferential airfoil spacing aerodynamic detuning. A combination of aerodynamic and structural detuning is considered. Relative flutter stability enhancements are assessed for a twelve-blade baseline rotor.
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Fleeter et al. (1989) studied this question.
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