Abstract
This study is to investigate the stall flutter of high-speed rotating blade section of small-scale blades subjected to combined flap-lag motion. The work is motivated by destructive flapwise vibrations of small-scale blades. The aeroelastic governing equations combine a spring-mass-damper equivalent of the structure and a nonlinear aerodynamic model suitable for pure pitching motion. The nonlinear resulting equations are solved by linearization and time-marching approach. The stall flutter stability characteristics are investigated, with flutter suppression discussed.
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