Multiblock Navier-Stokes solver for wing/fuselage transport aircraft

Guowei Yang, Masahiro Kondo, Shigeru Obayashi

Research output: Contribution to journalArticlepeer-review

11 Citations (Scopus)


An implicit multiblock Navier-Stokes solver, which contains the LU-SGS subiteration method and the HLLEW scheme, has been developed for numerical simulations on complex and realistic aerodynamic configurations. Two-level halo cells are used to communicate data between abutting blocks. The transfinite interpolation (TFI) and the elliptic method with boundary control are employed to generate the initial multiblock grid and to smooth the grid distribution in each block. A comparison is first done for the AGARD supercritical LANN-wing with single- and multi-block grids. Then the present method is applied to a NASA transport wing/fuselage configuration and the NAL supersonic transport (SST) model. The choice of multiblock grid topology from the view of aeroelastic calculation and the comparison of Euler and Navier-Stokes solutions are investigated.

Original languageEnglish
Pages (from-to)85-90
Number of pages6
JournalJSME International Journal, Series B: Fluids and Thermal Engineering
Issue number1
Publication statusPublished - 2002 Feb


  • Multiblock grid
  • Navier-Stokes equations
  • Numerical simulation

ASJC Scopus subject areas

  • Mechanical Engineering
  • Physical and Theoretical Chemistry
  • Fluid Flow and Transfer Processes


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