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

Koji Miyaji, Rei Nagasawa

抄録

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.

本文言語英語
ページ(範囲)18-26
ページ数9
ジャーナルTransactions of the Japan Society for Aeronautical and Space Sciences
60
1
ジャーナル掲載日出版済み - 2017

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

Keywords

    ASJC Scopus subject areas

    • Aerospace Engineering
    • Space and Planetary Science

    これを引用

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    N2 - 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.

    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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