The aerodynamic coefficients obtained from the analysis developed in Part I of this paper are utilized here to investigate stability and flutter boundaries for loaded cascades of airfoils with finite thickness. Combined bending and torsional oscillations for different stiffness ratios are studied for compressor and turbine cascades. The results show very significant effects of blade geometry and mean flow incidence on the stability and flutter boundaries. These effects are basically the consequence of strong coupling between the steady and unsteady aerodynamics of the cascade.

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