Abstract
An investigation of the influence of shock motion on flutter of rotors and cascades is presented. The present paper illustrates how a perturbation scheme can be used to calculate the nonlinear effects due to thickness, camber, and incidence to second order in a perturbation parameter. An approximate theory is also given, that accounts for the first-order quasisteady effects of shock motion and also allows experimentally determined shock structures and parameters to be used. The unsteady aerodynamic forces resulting from shock movements are shown to have a pronounced effect on the flutter boundaries of cascades representative of large fan rotors. Both stabilizing and destabilizing effects are observed, depending on interblade phase angle and shock structure. At low reduced frequencies, the shock-induced loads can destabilize bending oscillations sufficiently to cause single-degree-of-freedom bending flutter. It is also possible to explain the stabilizing effect of the back pressure on supersonic rotor flutter, as observed experimentally. a c CLV> CMV k k L m M M2 N P
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