TY - GEN
T1 - LES of full aircraft configuration using non-dissipative KEEscheme with conservative explicit filter
AU - Asada, Hiroyuki
AU - Kawai, Soshi
N1 - Funding Information:
This work was supported in part by MEXT as “Program for Promoting Researches on the Supercomputer Fugaku” (Leading research on innovative aircraft design technologies to replace flight test, JPMXP1020200312) and used computational resources of supercomputer Fugaku provided by RIKEN Center for Computational Science (Project ID: hp200137, hp210168).
Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2022
Y1 - 2022
N2 - Wall-modeled LES of full aircraft configuration is performed using non-dissipative kinetic energy and entropy preserving (KEEP) scheme with conservative explicit low-pass filter. The present wall-modeled LES is conducted by our compressible flow solver named FFVHC-ACE. The hierarchical Cartesian grid is used in this solver, and the wall-modeling on non-body-conforming boundaries (Tamaki and Kawai, Physical Review of Fluids, 2021) is employed. The stable and non-dissipative KEEP scheme (Kuya and Kawai, Journal of Computational Physics, 2018) is also used to achieve high-fidelity simulations, and the spurious oscillations induced by the KEEP scheme are removed by the conservative low-pass filter on the hierarchical Cartesian grid. The number of grid points is approximately 20 billion, and the massively parallel computations are conducted using the supercomputer "Fukgaku". The separation, pressure distributions, and lift coefficient of the full aircraft configuration at the near-stall condition are successfully predicted by the present wall-modeled LES with the KEEP scheme.
AB - Wall-modeled LES of full aircraft configuration is performed using non-dissipative kinetic energy and entropy preserving (KEEP) scheme with conservative explicit low-pass filter. The present wall-modeled LES is conducted by our compressible flow solver named FFVHC-ACE. The hierarchical Cartesian grid is used in this solver, and the wall-modeling on non-body-conforming boundaries (Tamaki and Kawai, Physical Review of Fluids, 2021) is employed. The stable and non-dissipative KEEP scheme (Kuya and Kawai, Journal of Computational Physics, 2018) is also used to achieve high-fidelity simulations, and the spurious oscillations induced by the KEEP scheme are removed by the conservative low-pass filter on the hierarchical Cartesian grid. The number of grid points is approximately 20 billion, and the massively parallel computations are conducted using the supercomputer "Fukgaku". The separation, pressure distributions, and lift coefficient of the full aircraft configuration at the near-stall condition are successfully predicted by the present wall-modeled LES with the KEEP scheme.
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U2 - 10.2514/6.2022-0449
DO - 10.2514/6.2022-0449
M3 - Conference contribution
AN - SCOPUS:85122911819
SN - 9781624106316
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
BT - AIAA SciTech Forum 2022
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
Y2 - 3 January 2022 through 7 January 2022
ER -