**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.