TY - GEN
T1 - Simulation of vortex pair instabilities behind a split wing
AU - Saulgeot, Pierre
AU - Brion, Vincent
AU - Navrose,
AU - Bonne, Nicolas
AU - Jacquin,
AU - Dormy, Emmanuel
N1 - Publisher Copyright:
© 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2023/1/1
Y1 - 2023/1/1
N2 - The dynamics of a pair of counter-rotating wingtip vortices formed in the wake of a slotted wing are investigated numerically at Reynolds numbers 3000 to 10 000, considering a NACA12 airfoil with various angles of attack ranging from 5 to 10 degrees. Two parts of the wake are investigated. Firstly, we focus on the von Kármán wake of the wing and explore its properties in reference to inifinite wing results. The finiteness of the wing introduces notable differences. Secondly, we examine the dynamics of the wingtip vortices and the instabilities that are obtained. The influence of the von Kármán wake on this vortex is emphasized. Two behaviors are identified, depending on the angle of attack and Reynolds number. An orthogonal proper orthogonal decomposition (POD) is applied to identify the coherent structures that superimpose upon the mean flow. A Fourier analysis of the vortex centerline is conducted to highlight the dominant wavelengths.
AB - The dynamics of a pair of counter-rotating wingtip vortices formed in the wake of a slotted wing are investigated numerically at Reynolds numbers 3000 to 10 000, considering a NACA12 airfoil with various angles of attack ranging from 5 to 10 degrees. Two parts of the wake are investigated. Firstly, we focus on the von Kármán wake of the wing and explore its properties in reference to inifinite wing results. The finiteness of the wing introduces notable differences. Secondly, we examine the dynamics of the wingtip vortices and the instabilities that are obtained. The influence of the von Kármán wake on this vortex is emphasized. Two behaviors are identified, depending on the angle of attack and Reynolds number. An orthogonal proper orthogonal decomposition (POD) is applied to identify the coherent structures that superimpose upon the mean flow. A Fourier analysis of the vortex centerline is conducted to highlight the dominant wavelengths.
UR - https://www.scopus.com/pages/publications/85199765231
U2 - 10.2514/6.2023-3889
DO - 10.2514/6.2023-3889
M3 - Conference contribution
AN - SCOPUS:85199765231
SN - 9781624107047
T3 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
BT - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
Y2 - 12 June 2023 through 16 June 2023
ER -