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@INBOOK{Cetin:866750,
      author       = {Cetin, Mehmet Onur and Pogorelov, Alexej and Lintermann,
                      Andreas and Cheng, Hsun-Jen and Meinke, Matthias and
                      Schröder, Wolfgang},
      title        = {{L}arge-{S}cale {S}imulations of a {N}on-generic
                      {H}elicopter {E}ngine {N}ozzle and a {D}ucted {A}xial {F}an},
      address      = {Cham},
      publisher    = {Springer International Publishing},
      reportid     = {FZJ-2019-05819},
      isbn         = {978-3-319-24631-4},
      pages        = {389-405},
      year         = {2016},
      comment      = {High Performance Computing in Science and Engineering ´15
                      / Nagel, Wolfgang E. (Editor) ; Cham : Springer
                      International Publishing, 2016, Chapter 25 ; ISBN:
                      978-3-319-24631-4 ; doi:10.1007/978-3-319-24633-8},
      booktitle     = {High Performance Computing in Science
                       and Engineering ´15 / Nagel, Wolfgang
                       E. (Editor) ; Cham : Springer
                       International Publishing, 2016, Chapter
                       25 ; ISBN: 978-3-319-24631-4 ;
                       doi:10.1007/978-3-319-24633-8},
      abstract     = {Large-eddy simulations (LESs) of a helicopter engine jet
                      and an axial fan are performed by using locally refined
                      Cartesian hierarchical meshes. For the computations a
                      high-fidelity, massively parallelized solver for
                      compressible flow is used. To verify the numerical method, a
                      coaxial hot round jet is computed and the results are
                      compared to reference data. The analysis is complemented by
                      a grid convergence study for both applications, i.e., for
                      the helicopter engine jet and the axial fan. For the
                      helicopter engine jet, additional computations have been
                      performed for two different nozzle geometries, i.e., a
                      simplified nozzle geometry that is consisting of a center
                      body and divergent outer annular channel, and a complete
                      engine nozzle geometry with 4 additional struts were used.
                      The presence of the struts results in a different potential
                      core break-down and turbulence intensity. Furthermore, for
                      the axial fan configuration, computations have been
                      performed at two different volume flow rates. The reduction
                      of the volume flow rate results in an interaction of the
                      tip-gap vortex with the neighboring blade which leads to a
                      higher turbulent kinetic energy near and inside the tip-gap
                      region.},
      pnm          = {511 - Computational Science and Mathematical Methods
                      (POF3-511)},
      pid          = {G:(DE-HGF)POF3-511},
      typ          = {PUB:(DE-HGF)7},
      doi          = {10.1007/978-3-319-24633-8_25},
      url          = {https://juser.fz-juelich.de/record/866750},
}