In this work a Discontinuos Galerkin (DG) solver for the incompressible Navier-Stokes equations has been extended to deal with the Reynolds-Averaged Navier-Stokes (RANS) equations coupled with the k-. ω turbulence model. A distinguishing feature of the method is the formulation of the inviscid interface numerical fluxes, based on an exact Riemann solver for the incompressible Euler equations with a relaxed incompressibility constraint. The turbulence model has been implemented in a non-standard way employing the variable ω~=logω instead of ω and enforcing the fulfilment of realizability conditions for the modeled turbulent stresses.The reliability, robustness and accuracy of the proposed implementation have been assessed by computing several turbulent test cases: (i) the flow past a flat plate for a Reynolds number Re = 11.1 × 106, (ii) the flow around a NACA 0012 airfoil at different angles of attack α=0°,10°,15° and Reynolds numbers Re=2.88×106,6.0×106, with comparisons with experimental and CFD benchmark data, and (iii) the flow through a rotating vertical axis wind turbine.

A high-order Discontinuous Galerkin solver for the incompressible RANS and k-ω turbulence model equations

GHIDONI, Antonio;REBAY, Stefano;
2014-01-01

Abstract

In this work a Discontinuos Galerkin (DG) solver for the incompressible Navier-Stokes equations has been extended to deal with the Reynolds-Averaged Navier-Stokes (RANS) equations coupled with the k-. ω turbulence model. A distinguishing feature of the method is the formulation of the inviscid interface numerical fluxes, based on an exact Riemann solver for the incompressible Euler equations with a relaxed incompressibility constraint. The turbulence model has been implemented in a non-standard way employing the variable ω~=logω instead of ω and enforcing the fulfilment of realizability conditions for the modeled turbulent stresses.The reliability, robustness and accuracy of the proposed implementation have been assessed by computing several turbulent test cases: (i) the flow past a flat plate for a Reynolds number Re = 11.1 × 106, (ii) the flow around a NACA 0012 airfoil at different angles of attack α=0°,10°,15° and Reynolds numbers Re=2.88×106,6.0×106, with comparisons with experimental and CFD benchmark data, and (iii) the flow through a rotating vertical axis wind turbine.
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11379/453927
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