TY - GEN
T1 - Morphing blade fluid-structure interaction
AU - Daynes, Stephen
AU - Weaver, Paul M.
PY - 2012
Y1 - 2012
N2 - 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.
AB - 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.
UR - http://www.scopus.com/inward/record.url?scp=84880800626&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/record.url?scp=84881422871&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84881422871
SN - 9781600869372
T3 - 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference 2012
BT - 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference 2012
T2 - 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference 2012
Y2 - 23 April 2012 through 26 April 2012
ER -