Marc Braune, Anne Hebler

DOI Number: N/A

Conference number: IFASD-2019-132

Results of a flutter experiment on a CAST 10 supercritical laminar airfoil with an experimentally specified degree of freedom in pitch are presented. On the basis of a selected limit cycle oscillation, the underlying unsteady flow effects are analysed. In addition to a resolution of the movement and the temporal behavior of the laminar-turbulent boundary layer transition as well as the movement of the compression shock, the shock-boundary layer interaction is discussed in detail. An analysis of the energy transfer establishes a connection between the previously discussed flow effects and possible causes for the aeroelastic instability as well as the limitation of the amplitude of the observed LCOs. A phase lead of the boundary layer transition in relation to the shock motion occurs. This is associated with a change of the phase difference between the aerodynamic moment and the pitch motion of the laminar airfoil during the onset and growth of limit cycle oscillation, which contributes significantly to the limitation of the LCO amplitude. In addition, a connection between the movement of the boundary layer transition and a positive energy input into the structure is indicated.

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In Categories: IFASD 2019, Unsteady Laminar Flow
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