INTRODUCTION


 


            This project is based on Airfoil calculation with the AVBP code. This simulating code from
CERFACS solves compressible Navier-Stokes equations in 2D structured and unstructured meshes.
This solver is well adapted to combustion or aerodynamic calculation.
 
        The aim of this project is to study the influence of numerical parameters on the calculation and to
determine the polar (pressure coefficient Cp as function of alpha, with alpha being the angle of attack).

        This study is composed of three parts. At first we will study the influence of numerical parameters
on the calculation with the Bump test. Then we will compare three different meshes in Airfoil computation.
And finnally, we will study the influence of the angle of attack in order to determine the polar.
 

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