Numerical investigation of blade-tip-vortex dynamics
Numerical computations on a finite wing are carried out using DLR’s finite-volume solver TAU. The tip-vortex characteristics during static stall and deep dynamic stall are analyzed and compared to particle image velocimetry (PIV) measurements carried out in the side wind facility Göttingen. Computat...
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| Veröffentlicht in: | CEAS aeronautical journal 2018-09, Vol.9 (3), p.373-386 |
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| creator | Kaufmann, Kurt Wolf, C. Christian Merz, Christoph B. Gardner, Anthony D. |
| description | Numerical computations on a finite wing are carried out using DLR’s finite-volume solver TAU. The tip-vortex characteristics during static stall and deep dynamic stall are analyzed and compared to particle image velocimetry (PIV) measurements carried out in the side wind facility Göttingen. Computational fluid dynamics (CFD) and experiment are in good agreement, especially for sections close to the blade tip. Too large dissipation within the numerical computations leads to larger vortex size than in the experiment. The dissipation effect increases with larger distances from the wing. The analysis shows that the numerical method is able to capture the complex vortex structures shed from the wing and helps understanding the source of these structures. |
| doi_str_mv | 10.1007/s13272-018-0287-2 |
| format | Article |
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Christian</creatorcontrib><creatorcontrib>Merz, Christoph B.</creatorcontrib><creatorcontrib>Gardner, Anthony D.</creatorcontrib><title>Numerical investigation of blade-tip-vortex dynamics</title><title>CEAS aeronautical journal</title><addtitle>CEAS Aeronaut J</addtitle><description>Numerical computations on a finite wing are carried out using DLR’s finite-volume solver TAU. The tip-vortex characteristics during static stall and deep dynamic stall are analyzed and compared to particle image velocimetry (PIV) measurements carried out in the side wind facility Göttingen. Computational fluid dynamics (CFD) and experiment are in good agreement, especially for sections close to the blade tip. Too large dissipation within the numerical computations leads to larger vortex size than in the experiment. The dissipation effect increases with larger distances from the wing. 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| subjects | Aerospace Technology and Astronautics Computational fluid dynamics Dissipation Engineering Numerical analysis Numerical methods Original Paper Particle image velocimetry Velocity measurement Vortices |
| title | Numerical investigation of blade-tip-vortex dynamics |
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