Marc Braune, Anne Hebler

DOI Number: N/A

Conference number: IFASD-2019-133

Results of an experimental bifurcation analysis, obtained during a 2D flutter experiment in transonic flow on a CAST 10-2 supercritical laminar airfoil with one experimentally specified degree of freedom in pitch are presented. The nonlinear system response for a variation of the Mach number and the mean angle of attack is investigated. Subcritical bifurcations and hystereses occur for both bifurcation parameters. The observed LCOs occur in the vicinity of the laminar drag bucket and are associated with significant changes in frequencies and phase differences between airfoil motion and aerodynamic forces. The results indicate a strong correlation between the shock-boundary layer interaction and the observed aeroelastic instability.

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In Categories: IFASD 2019, Unsteady Laminar Flow
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