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2009•Journal of Chongqing Institute of TechnologyRequires access

Numerical Simulation on Aerodynamic Performance of General Airfoil

Wang Xu-dong

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Abstract

2D physical and mathematical model is built to simulate the flow around an airfoil,the steady compressible Reynolds-Averaged Navier-Stokes equations are solved numerically and Spalart-Allmaras turbulence model is applied to solve the turbulent viscosity using the CFD commercial software called FLUENT.The coefficients of lift and drag as well as the pressure distribution are concluded with the change of angle of flow attack for airfoil at Reynolds number of 3.2e+06.The comparison between computed results and similar airfoil' experimental data show that results using Spalart-Allmaras turbulence model are closer to experimental results,and the airfoil has higher lift coefficient and higher lift-drag ratio.

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What this paper is about

2D physical and mathematical model is built to simulate the flow around an airfoil,the steady compressible Reynolds-Averaged Navier-Stokes equations are solved numerically and Spalart-Allmaras turbulence model is applied to solve the turbulent viscosity using the CFD commercial software called FLUENT.The coefficients of lift and drag as well as the pressure distribution are concluded with the change of angle of flow attack for airfoil at Reynolds number of 3.2e+06.The comparison between computed results and similar airfoil' experimental data show that results using Spalart-Allmaras turbulence model are closer to experimental results,and the airfoil has higher lift coefficient and higher lift-drag ratio.

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Available abstract

2D physical and mathematical model is built to simulate the flow around an airfoil,the steady compressible Reynolds-Averaged Navier-Stokes equations are solved numerically and Spalart-Allmaras turbulence model is applied to solve the turbulent viscosity using the CFD commercial software called FLUENT.The coefficients of lift and drag as well as the pressure distribution are concluded with the change of angle of flow attack for airfoil at Reynolds number of 3.2e+06.The comparison between computed results and similar airfoil' experimental data show that results using Spalart-Allmaras turbulence model are closer to experimental results,and the airfoil has higher lift coefficient and higher lift-drag ratio.

Key concepts: Airfoil, Turbulence, Lift coefficient, Mechanics, Lift (data mining), Aerodynamics, Lift-to-drag ratio, Angle of attack

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