Fluid-structure interactions for flexible and rigid tandem-wings at low Reynolds numbers

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Force, Particle Image Velocimetry, Digital Image Correlation and hot-wire measurements were performed for two flat rectangular wings of semi-aspect-ratio 2 in tandem configurations. The wings were separated by a streamwise distance of 1.5 chord lengths at 30° angle of attack and Reynolds number 100,000. The crosswise wing separation was varied systematically from -1.5 to 1.5 chord lengths. A rigid-leading rigid-trailing (R-R) wing configuration and a flexible-leading rigid-trailing (F-R) wing configuration were considered. Crosswise wing separations for the F-R case between 0.0 to 0.4 chord lengths were shown to increase lift coefficient relative to the R-R case; the main benefit in lift generation was noted for the trailing-wing. For the F-R configuration, spanwise deformation of the leading-flexible wing shifted the impingement point of the trailing-edge shear layer on the trailing-wing thus affecting lift generation. Deformation measurements showed that the presence of the rigid-trailing-wing had a profound influence on the flow-induced vibrations of the leading-flexible-wing, peaking at a crosswise separation of 0.32 chord lengths which also provided the largest unsteady forces. Velocity spectra measurements revealed that cases producing increased unsteady forces possessed distinct inter-wing velocity fluctuations which were coupled with the wing vibrations. The results demonstrate that the time-averaged forces and unsteady fluid-structure interactions are strongly determined by the crosswise wing separation and the spanwise flexibility of the leading-wing in tandem configurations.
LanguageEnglish
Title of host publication53rd AIAA Aerospace Sciences Meeting
Subtitle of host publicationAIAA SciTech
PublisherAmerican Institute of Aeronautics and Astronautics
DOIs
StatusPublished - 2015
Event53rd AIAA Aerospace Sciences Meeting (AIAA SciTech 2015) - Kissimmee, Florida, USA United States
Duration: 5 Jan 2015 → …

Conference

Conference53rd AIAA Aerospace Sciences Meeting (AIAA SciTech 2015)
CountryUSA United States
CityKissimmee, Florida
Period5/01/15 → …

Fingerprint

Fluid structure interaction
Reynolds number
Rigid wings
Flexible wings
Angle of attack
Velocity measurement
Aspect ratio
Wire

Cite this

Jones, R., Cleaver, D., & Gursul, I. (2015). Fluid-structure interactions for flexible and rigid tandem-wings at low Reynolds numbers. In 53rd AIAA Aerospace Sciences Meeting: AIAA SciTech American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.2015-1752

Fluid-structure interactions for flexible and rigid tandem-wings at low Reynolds numbers. / Jones, Robin; Cleaver, David; Gursul, Ismet.

53rd AIAA Aerospace Sciences Meeting: AIAA SciTech. American Institute of Aeronautics and Astronautics, 2015.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Jones, R, Cleaver, D & Gursul, I 2015, Fluid-structure interactions for flexible and rigid tandem-wings at low Reynolds numbers. in 53rd AIAA Aerospace Sciences Meeting: AIAA SciTech. American Institute of Aeronautics and Astronautics, 53rd AIAA Aerospace Sciences Meeting (AIAA SciTech 2015), Kissimmee, Florida, USA United States, 5/01/15. https://doi.org/10.2514/6.2015-1752
Jones R, Cleaver D, Gursul I. Fluid-structure interactions for flexible and rigid tandem-wings at low Reynolds numbers. In 53rd AIAA Aerospace Sciences Meeting: AIAA SciTech. American Institute of Aeronautics and Astronautics. 2015 https://doi.org/10.2514/6.2015-1752
Jones, Robin ; Cleaver, David ; Gursul, Ismet. / Fluid-structure interactions for flexible and rigid tandem-wings at low Reynolds numbers. 53rd AIAA Aerospace Sciences Meeting: AIAA SciTech. American Institute of Aeronautics and Astronautics, 2015.
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AB - Force, Particle Image Velocimetry, Digital Image Correlation and hot-wire measurements were performed for two flat rectangular wings of semi-aspect-ratio 2 in tandem configurations. The wings were separated by a streamwise distance of 1.5 chord lengths at 30° angle of attack and Reynolds number 100,000. The crosswise wing separation was varied systematically from -1.5 to 1.5 chord lengths. A rigid-leading rigid-trailing (R-R) wing configuration and a flexible-leading rigid-trailing (F-R) wing configuration were considered. Crosswise wing separations for the F-R case between 0.0 to 0.4 chord lengths were shown to increase lift coefficient relative to the R-R case; the main benefit in lift generation was noted for the trailing-wing. For the F-R configuration, spanwise deformation of the leading-flexible wing shifted the impingement point of the trailing-edge shear layer on the trailing-wing thus affecting lift generation. Deformation measurements showed that the presence of the rigid-trailing-wing had a profound influence on the flow-induced vibrations of the leading-flexible-wing, peaking at a crosswise separation of 0.32 chord lengths which also provided the largest unsteady forces. Velocity spectra measurements revealed that cases producing increased unsteady forces possessed distinct inter-wing velocity fluctuations which were coupled with the wing vibrations. The results demonstrate that the time-averaged forces and unsteady fluid-structure interactions are strongly determined by the crosswise wing separation and the spanwise flexibility of the leading-wing in tandem configurations.

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