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Ingénierie et systèmes   > Accueil   > Incertitudes et fiabilité des systèmes multiphysiques   > Numéro 2   > Article

Analyse CFD de l’écoulement transsonique autour d’un profil d’aile NACA 0012

CFD Analysis of the Transonic Flow over a NACA 0012 Airfoil


R. El Maani
INSA de Rouen

B. Radi
LIMII FST Settat
Maroc

A. El Hami
INSA de Rouen



Publié le 14 décembre 2018   DOI : 10.21494/ISTE.OP.2018.0307

Résumé

Abstract

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Computational Fluid Dynamics (CFD) incorporates mathematical relations and algorithms to analyze and solve the problems regarding fluid flow. CFD analysis of an airfoil produces results such as lift and drag forces which determines the ability of an airfoil. In this paper a transonic flow will be modelled over a NACA 0012 airfoil for which experimental data has been published, so that a comparison can be made. The flow to be considered is compressible and turbulent and the solver used is the density based implicit solver, which gives good results for high speed compressible flows. The results show that the predicted lift, drag and pressure coefficients are in good agreement with experimental data.

Computational Fluid Dynamics (CFD) incorporates mathematical relations and algorithms to analyze and solve the problems regarding fluid flow. CFD analysis of an airfoil produces results such as lift and drag forces which determines the ability of an airfoil. In this paper a transonic flow will be modelled over a NACA 0012 airfoil for which experimental data has been published, so that a comparison can be made. The flow to be considered is compressible and turbulent and the solver used is the density based implicit solver, which gives good results for high speed compressible flows. The results show that the predicted lift, drag and pressure coefficients are in good agreement with experimental data.

CFD aerodynamic NACA 0012 pressure coefficient airfoil

CFD aerodynamic NACA 0012 pressure coefficient airfoil