TY - GEN
T1 - Computations of Flow past a Three-Element 30P30N Airfoil Using Wray-Agarwal One Equation Turbulence Model
AU - Hendrickson, Karsten
AU - Agarwal, Ramesh K.
N1 - Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.
PY - 2021
Y1 - 2021
N2 - The predictions of flow phenomenon that occur in high lift systems have proven to be challenging using the Reynolds-Averaged Navier-Stokes (RANS) equations with turbulence models. The complex interactions that occur among different elements of the wing can be difficult for turbulence models to accurately predict. Results from the recently developed Wray-Agarwal (WA) one-equation turbulence model, the frequently used Spalart-Allmaras (SA) and shear stress transport (SST) k-ω turbulence models are compared to experimental results to evaluate each model’s relative accuracy. It is shown that at lower angles of attack the computed lift from each turbulence model has similar accuracy as in the experimentally determined lift. At higher angles of attack the WA model shows decreased accuracy while the SA and SST k-ω have similar accuracy. For other computed flow field quantities, the experimental data generally matches closest to the results from the SA model on a fine grid. In some cases, the WA and SST k-ω model have improved accuracy over the SA model on the same grid.
AB - The predictions of flow phenomenon that occur in high lift systems have proven to be challenging using the Reynolds-Averaged Navier-Stokes (RANS) equations with turbulence models. The complex interactions that occur among different elements of the wing can be difficult for turbulence models to accurately predict. Results from the recently developed Wray-Agarwal (WA) one-equation turbulence model, the frequently used Spalart-Allmaras (SA) and shear stress transport (SST) k-ω turbulence models are compared to experimental results to evaluate each model’s relative accuracy. It is shown that at lower angles of attack the computed lift from each turbulence model has similar accuracy as in the experimentally determined lift. At higher angles of attack the WA model shows decreased accuracy while the SA and SST k-ω have similar accuracy. For other computed flow field quantities, the experimental data generally matches closest to the results from the SA model on a fine grid. In some cases, the WA and SST k-ω model have improved accuracy over the SA model on the same grid.
UR - http://www.scopus.com/inward/record.url?scp=85126747182&partnerID=8YFLogxK
U2 - 10.2514/6.2021-2611
DO - 10.2514/6.2021-2611
M3 - Conference contribution
AN - SCOPUS:85126747182
SN - 9781624106101
T3 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
BT - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
Y2 - 2 August 2021 through 6 August 2021
ER -