MISER2 computer program calculates flutter boundaries and aeroelastic response of cascade of arbitrarily mistuned airfoils. Based on typical section formulation incorporating incompressible, subsonic and supersonic cascade, unsteady aerodynamic theories. Each blade modeled as two-degree-of-freedom oscillator that has inertial coupling between bending and torsional motions. Written in FORTRAN 4.
Computing Flutter Boundaries
NASA Tech Briefs ; 13 , 4
01.04.1989
Sonstige
Keine Angabe
Englisch
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