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- W2024887008 abstract "An unsteady, two-dimensional, incompressible potentialow solver and an unsteady, two-dimensional, compressible Euler/Navier-Stokes ow solver are coupled with a two-degree-of-freedom structural model for the time-domain computation of aeroelastic response. Comparisons are made between results from the two ow solvers and with utter boundary predictions of linear theory. Presented results demonstrate similar destabilizing e ects for both increasing airfoil thickness and increasing Mach number. More importantly, it is shown that linear theory yields un-conservative utter-velocity predictions. While linear theory predicts that single-degree-of-freedom (pitching) utter cannot occur except with an unrealistically high sectional moment of inertia, it is shown here that thicker airfoils in compressible ows may easily achieve singledegree-of-freedom utter under realistic conditions." @default.
- W2024887008 created "2016-06-24" @default.
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- W2024887008 date "1998-01-12" @default.
- W2024887008 modified "2023-10-16" @default.
- W2024887008 title "Airfoil geometry and flow compressibility effects on wings and blade flutter" @default.
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- W2024887008 doi "https://doi.org/10.2514/6.1998-517" @default.
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