Morphing blade fluid-structure interaction

Stephen Daynes, Paul M. Weaver

Research output: Chapter in Book/Report/Conference proceedingConference Contribution (Conference Proceeding)

7 Citations (Scopus)


Wind tunnel tests have been conducted on a 1.3 m chord NACA 63-418 blade section fitted with an adaptive trailing edge flap. The 20% chord flap has an aramid honeycomb core covered with a silicone skin and is actuated using servo motors. The honeycomb core has a high stiffness in the thickness direction but is compliant in flapwise bending. These anisotropic properties offer a potential solution for the conflicting design requirements found in morphing trailing edge structures. Static and dynamic tests were performed on the adaptive blade section up to a Reynolds number of 5.4×106. Tests have shown that deflecting the flap from -10° to +10° changes the blade section lift coefficient by 1.0 in non-stalled conditions. Dynamic tests have shown the flap to be capable of operating up to 9°/s using a 15 V power supply. A two-dimensional static aeroelastic model of the morphing flap was developed to analyze strains, predict actuator requirements and study fluid-structure interaction effects. The model was used to conduct parametric studies to further improve the flap design. Potential applications include wind turbine blade load alleviation and increased wind energy capture.

Original languageEnglish
Title of host publication53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference 2012
Publication statusPublished - 1 Dec 2012
Event53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference - Honolulu, HI, United States
Duration: 23 Apr 201226 Apr 2012


Conference53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Country/TerritoryUnited States
CityHonolulu, HI


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