Double linearization theory applied to unsteady aerodynamic analysis of 2-dimensional supersonic cascade vibrating with finite mean loading.

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An extension of the improved double linearization theory to two-dimensional supersonic cascades is presented to predict the mean loading effects on unsteady aerodynamic forces on blades in vibrating motion. In the case of supersonic cascades, the aerodynamic instability of the blade motion is significantly affected by the effect of the unsteady displacement of shock reflection points which appear as a fluctuating concentrated force acting at a mean reflection point. Sample results illustrating the effects of blade angle of attack, camber, thickness, Mach number and pitch-chord ratio on the unsteady aerodynamic response are presented.