« contribution a l’étude numérique de l’écoulement subsonique et transsonique autour d’un profil d’aile mince type NACA 0006 »


The works allows to studying theoretically (numerical method + solver Fluent)
the flow around the profile. Our attention will be principally takes on the
description of the parallel and homogeneous flow. In the same context and in
the case of the potential flow, we will take the perturbed function φ caused by
the presence of the profile. The mathematical formulation of the problem gives
for different Mach number several forms of differential equations as (linear or
non linear). The solution found for each Mach number interval allows a good
understanding of the flow behaviors inside the studies field.

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