Analysis of supersonic stall bending flutter in axial-flow compressor by actuator disk theory
John J. Adamczyk, Lewis Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office
National Aeronautics and Space Administration, Scientific and Technical Information Office, 1978 - Medical - 55 pages
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85 percent 90 Weight flow actuator disk theory aerodynamic force aeroelastic airfoil analysis predicts axial-flow compressors bending flutter mode boundary condition C±oo calculated cascade plane complex constant control volume damping level deformed cascade design Figure design wheel speed deviation-angle correlation downstream enthalpy entropy exit flow angle flow and wheel flow field flow separation flow variables function of interblade function of weight high-speed fan stages inlet conditions inlet pressure interblade phase angle inviscid l,oo measured flutter boundary mechanical damping NASA two-stage fan nondimensional normalized aerodynamic damping normalized damping onset of flutter onset of supersonic order yields percent of design percent of span performance map predicted flutter boundaries predicting the onset radians reduced frequency rotor assembly rotor blade rotor system shock wave shown in figure solid symbol stability boundary stall bending flutter stall line steady flow steady-state supersonic stall bending supersonic stall flutter unsteady vector potential vorticity WRel