TY - GEN
T1 - Wall-Modeled Large-Eddy Simulation with Second-Order Accurate Upwind Scheme
AU - Yasuda, Hidemasa
AU - Kawai, Soshi
N1 - Funding Information:
This work was supported in part by Japan New Energy and Industrial Technology Development Organization (NEDO) project; Development of Numerical Simulation Methods for Cost-Effective Aircraft Design, subject 7; High-Fidelity Unsteady Computational Fluid Dynamics around Outer Range of Flight Envelope.
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.
PY - 2021
Y1 - 2021
N2 - On aircraft aerodynamic design, wall-modeled large-eddy simulation (WMLES) is expected to improve accuracy of simulation on unsteady flow field such as transonic buffet on aircraft wing. This is essential to simulate flow around an aircraft across the full flight envelope with high fidelity. In this study, three requirements are proposed to ensure accuracy of WMLES with second-order accurate scheme, which is commonly used to treat highly complicated geometry with unstructured grid system. These requirements are related to 1) matching point height, 2) matching point cell index, and 3) grid resolution at the matching point, where matching point is overlap point of LES and the wall model. These requirements are validated on flat-plate turbulent boundary layer and shock/boundary-layer interaction flow. As a result, it is clarified that all of the proposed requirements are necessary to ensure the accuracy of mean velocity and Reynolds stresses.
AB - On aircraft aerodynamic design, wall-modeled large-eddy simulation (WMLES) is expected to improve accuracy of simulation on unsteady flow field such as transonic buffet on aircraft wing. This is essential to simulate flow around an aircraft across the full flight envelope with high fidelity. In this study, three requirements are proposed to ensure accuracy of WMLES with second-order accurate scheme, which is commonly used to treat highly complicated geometry with unstructured grid system. These requirements are related to 1) matching point height, 2) matching point cell index, and 3) grid resolution at the matching point, where matching point is overlap point of LES and the wall model. These requirements are validated on flat-plate turbulent boundary layer and shock/boundary-layer interaction flow. As a result, it is clarified that all of the proposed requirements are necessary to ensure the accuracy of mean velocity and Reynolds stresses.
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U2 - 10.2514/6.2021-2752
DO - 10.2514/6.2021-2752
M3 - Conference contribution
AN - SCOPUS:85126734232
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 -