TY - GEN
T1 - Predictability of wall-modeled les for reynolds number effects of airfoil flows at transonic buffet and near-stall conditions
AU - Fukushima, Yuma
AU - Tamaki, Yoshiharu
AU - Kawai, Soshi
N1 - Funding Information:
This work was supported in part by MEXT as a social and scientific priority issue (Development of Innovative Design and Production Processes that Lead the Way for the Manufacturing Industry in the Near Future) to be tackled by using post-K computer. A part of this research used computational resources of the K computer provided by the RIKEN Advanced Institute for Computational Science (Project ID:hp150254, hp160205, hp170267, hp180185, hp180158, hp190164).
Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - Wall-modeled large-eddy simulations at realistic high Reynolds numbers (Rec ≈ 107 ) are conducted to invesitgate the Reynolds number effect on the airfoil flow fields. Transonic airfoil flow fields around the OAT15A supercritical airfoil and near-stall flow fields around the A-airfoil are investigated based on our previous WMLES studies at experimental Reynolds number (Rec ≈ 106 ) [1, 2]. Results show that the WMLES qualitatively predicts the typical Reynolds number effect such as decrease of boundary layer thickness and increase of lift coefficient. The thin boundary layer thickness induces the backward displacement of the shock wave in the transonic case. In the near-stall case, also the laminar-turbulent transition location significantly affects the boundary layer thickness and the lift coefficients, and the accurate prediction of transition location is important in the prediction of the near-stall flow field.
AB - Wall-modeled large-eddy simulations at realistic high Reynolds numbers (Rec ≈ 107 ) are conducted to invesitgate the Reynolds number effect on the airfoil flow fields. Transonic airfoil flow fields around the OAT15A supercritical airfoil and near-stall flow fields around the A-airfoil are investigated based on our previous WMLES studies at experimental Reynolds number (Rec ≈ 106 ) [1, 2]. Results show that the WMLES qualitatively predicts the typical Reynolds number effect such as decrease of boundary layer thickness and increase of lift coefficient. The thin boundary layer thickness induces the backward displacement of the shock wave in the transonic case. In the near-stall case, also the laminar-turbulent transition location significantly affects the boundary layer thickness and the lift coefficients, and the accurate prediction of transition location is important in the prediction of the near-stall flow field.
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U2 - 10.2514/6.2020-1982
DO - 10.2514/6.2020-1982
M3 - Conference contribution
AN - SCOPUS:85092413815
SN - 9781624105951
T3 - AIAA Scitech 2020 Forum
SP - 1
EP - 10
BT - AIAA Scitech 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2020
Y2 - 6 January 2020 through 10 January 2020
ER -