Residual distribution method for high Reynolds number simulations on complex geometries

Residual distribution method for high Reynolds number simulations on complex geometries

•We apply the residual distribution method for the complex 3D wing-body geometry.•The residual distribution method is applied for the RANS-SA system of equations.•The method exploits truly multidimensional upwind.•The method is characterized by low numerical viscosity. In this paper the application...

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Bibliographic Details
Published in:Computers & fluids Vol. 166; pp. 104 - 116
Main Authors: Majewski, Jerzy, Szałtys, Piotr, Wyrozębski, Marcin
Format: Journal Article
Language:English
Published: Amsterdam Elsevier Ltd 30-04-2018
Elsevier BV
Subjects:
Aerodynamics
CFD
Complexity
Computational fluid dynamics
Computer simulation
Delta wings
Drag coefficients
Finite element method
Fluid flow
Geometry
High lift
High Reynolds number
Numerical methods
Partial differential equations
Residual Distribution Scheme
Reynolds number
Simulation
Stress concentration
Three dimensional bodies
Three dimensional flow
Turbulence modeling
CFD
Turbulence modeling
Residual Distribution Scheme
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Summary:•We apply the residual distribution method for the complex 3D wing-body geometry.•The residual distribution method is applied for the RANS-SA system of equations.•The method exploits truly multidimensional upwind.•The method is characterized by low numerical viscosity. In this paper the application and performance of a Residual Distribution Scheme (RDS) for high Reynolds number, turbulent simulations on complex geometries is presented. The RDS is a numerical method for solving Partial Differential Equations, alternative to the typically used Finite Element and Finite Volume methods. The RDS method has been already successfully applied for both 2D and 3D turbulent aerodynamic cases, however the geometries were of limited level of complexity - at most a 3D wing (e.g.: Onera M6, delta wing). In this paper a flow past a 3D wing-body geometry with extended slat and deflected flap configuration is investigated. The geometry is the one from the High Lift Prediction Workshop 1 (HLPW-1). The RDS results are presented and compared with contributions submitted to the HLPW-1 workshop. The comparison of the results shows that the RDS provides very accurate solution both in terms of pressure coefficient distribution, especially in a region near the wing-tip, as well as integral values (lift, drag coefficients).
ISSN:0045-7930
1879-0747
DOI:10.1016/j.compfluid.2018.01.028