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@ARTICLE{Lintermann:875379,
      author       = {Lintermann, Andreas and Schröder, Wolfgang},
      title        = {{L}attice–{B}oltzmann simulations for complex geometries
                      on high-performance computers},
      journal      = {CEAS Aeronautical Journal},
      volume       = {11},
      issn         = {1869-5590},
      address      = {Wien [u.a.]},
      publisher    = {Springer},
      reportid     = {FZJ-2020-01990},
      pages        = {745-766},
      year         = {2020},
      abstract     = {Complex geometries pose multiple challenges to the field of
                      computational fluid dynamics. Grid generation for intricate
                      objects is often difficult and requires accurate and
                      scalable geometrical methods to generate meshes for
                      large-scale computations. Such simulations, furthermore,
                      presume optimized scalability on high-performance computers
                      to solve high-dimensional physical problems in an adequate
                      time. Accurate boundary treatment for complex shapes is
                      another issue and influences parallel load-balance. In
                      addition, large serial geometries prevent efficient
                      computations due to their increased memory footprint, which
                      leads to reduced memory availability for computations. In
                      this paper, a framework is presented that is able to address
                      the aforementioned problems. Hierarchical Cartesian
                      boundary-refined meshes for complex geometries are obtained
                      by a massively parallel grid generator. In this process, the
                      geometry is parallelized for efficient computation.
                      Simulations on large-scale meshes are performed by a
                      high-scaling lattice–Boltzmann method using the
                      second-order accurate interpolated bounce-back boundary
                      conditions for no-slip walls. The method employs Hilbert
                      decompositioning for parallel distribution and is hybrid
                      MPI/OpenMP parallelized. The parallel geometry allows to
                      speed up the pre-processing of the solver and massively
                      reduces the local memory footprint. The efficiency of the
                      computational framework, the application of which to, e.g.,
                      subsonic aerodynamic problems is straightforward, is shown
                      by simulating clearly different flow problems such as the
                      flow in the human airways, in gas diffusion layers of fuel
                      cells, and around an airplane landing gear configuration},
      cin          = {JSC},
      ddc          = {620},
      cid          = {I:(DE-Juel1)JSC-20090406},
      pnm          = {511 - Computational Science and Mathematical Methods
                      (POF3-511) / Rhinodiagnost $(jhpc54_20180501)$},
      pid          = {G:(DE-HGF)POF3-511 / $G:(DE-Juel1)jhpc54_20180501$},
      typ          = {PUB:(DE-HGF)16},
      doi          = {10.1007/s13272-020-00450-1},
      url          = {https://juser.fz-juelich.de/record/875379},
}