Abstract
An improved structural dynamic model of an oscillating blade in two degrees of freedom is combined with an unsteady aerodynamic model for the transonic flow about a cascade with separation, which results in a coupled system. The system is solved in an iterative way between the two models. As a check on the current energy methods, the stall flutter boundaries for two real rotors are predicted by using the present method and the results are compared with the experiments and those predicted by using an energy method.
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Li, H., Sheng, Z. A check on the energy method of predicting blade transonic stall flutter. Acta Mech Sinica 2, 121–128 (1986). https://doi.org/10.1007/BF02485852
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DOI: https://doi.org/10.1007/BF02485852