Theoretical investigation of subsonic oscillatory blade-row aerodynamics

Frank Lane, Manfred Friedman
naca-tn-4136
Feb 1958


A method is presented for calculating the aerodynamic lifts and moments experienced by a cascade or two-dimensional approximation to a compressor or turbine blade row in subsonic flow under harmonic oscillation. Arbitrary stagger and interblade phase-lag angles are permitted. The most significant features of the method stem from the utilization of Fourier transforms of blade pressure-jump functions.

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