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Presentation
Stall Flutter Measurements from a Two-Degree-of-Freedom Airfoil with Nonlinear Stiffness
Proceedings of the 54th AIAA/ASME/ASCE/AHS Structures, Structural Dynamics, and Materials Conference (2013)
  • Ndungu Muturi
  • Alex Spies
  • Katherine Bender
  • Christopher Lee
Abstract

Results are presented from an experimental study of stall flutter oscillations from a two-degree-of-freedom, pitch/plunge airfoil system with nonlinear structural stiffness in the plunge direction. With linear (only) structural stiffness, the airfoil system could exhibit a large-pitch-amplitude limit cycle response which is attributed to stall. With the addition of the nonlinear stiffness, the airfoil system could exhibit two classes of limit cycle response: one with low-pitch-amplitude attributed to the structural nonlinearity and one with high-pitch-amplitude attributed to stall. The amplitudes of the limit cycles for cases in which the structurals and aerodynamic nonlinearities co-exist are modulated and remain steady over a range of airspeeds and for initial excitations above a critical value.

Keywords
  • stall behavior,
  • airfoil,
  • nonlinear stiffness
Publication Date
April 8, 2013
Comments

© 2013 American Institute of Aeronautics and Astronautics. This article was published as part of the Proceedings of the 54th AIAA/ASME/ASCE/AHS Structures, Structural Dynamics, and Materials Conference and can be found here.

Citation Information
Ndungu Muturi, Alex Spies, Katherine Bender and Christopher Lee. "Stall Flutter Measurements from a Two-Degree-of-Freedom Airfoil with Nonlinear Stiffness" Proceedings of the 54th AIAA/ASME/ASCE/AHS Structures, Structural Dynamics, and Materials Conference (2013)
Available at: http://works.bepress.com/christopher_lee/39/