Extension of the flux reconstruction method to high-reynolds number RANS simulations around high-lift devices

Koji Miyaji, Rei Nagasawa

Abstract

Spatially high-order flow simulations are conducted for high-Reynolds number flows around two-dimensional high-lift devices. The method uses a 'flux-reconstruction (FR) approach' that is applicable to unstructured quadrilateral or hexahedral grids. This is the first study focused on solving Reynolds-averaged Navier-Stokes equations coupled with k-ω turbulence model equations using the FR method. The performance of the turbulence model in the high-order scheme is first verified using standard benchmark problems. The flow around the three-element, high-lift airfoil known as NHLP/L1T2 is then tried. Simulations from second-order (solution polynomial degree 1, or p=1) to fourth-order (p=3) accuracy all predicted the surface pressure well, while the total pressure distribution in the wake was captured well by p=2 and p=3 simulations. The effects of new wall boundary conditions and minimum cell size are qualitatively discussed.

Original languageEnglish
Pages (from-to)18-26
Number of pages9
JournalTransactions of the Japan Society for Aeronautical and Space Sciences
Volume60
Issue number1
StatePublished - 2017

Fingerprint

Fluxes
Turbulence models
Reynolds number
Flow simulation
Airfoils
Pressure distribution
Navier Stokes equations
Polynomials
Boundary conditions

Keywords

  • CFD
  • High-Order Method
  • Turbulence Model

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

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AB - Spatially high-order flow simulations are conducted for high-Reynolds number flows around two-dimensional high-lift devices. The method uses a 'flux-reconstruction (FR) approach' that is applicable to unstructured quadrilateral or hexahedral grids. This is the first study focused on solving Reynolds-averaged Navier-Stokes equations coupled with k-ω turbulence model equations using the FR method. The performance of the turbulence model in the high-order scheme is first verified using standard benchmark problems. The flow around the three-element, high-lift airfoil known as NHLP/L1T2 is then tried. Simulations from second-order (solution polynomial degree 1, or p=1) to fourth-order (p=3) accuracy all predicted the surface pressure well, while the total pressure distribution in the wake was captured well by p=2 and p=3 simulations. The effects of new wall boundary conditions and minimum cell size are qualitatively discussed.

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