摘要：In this paper is presented the results obtained by means numerical simulations
of the flow over the NACA 0012 airfoil at different Mach numbers using two
codes: one developed at Instituto Tecnológico de Aeronáutica of Brazil (ITA);
the second developed at the Departamento de Aeronáutica de la Universidad
Nacional de Córdoba (UNC). The computer code developed at ITA works with a
boundary-fitted structured-grid context; and it solves the equations by a
finite-volume technique, using three different time-marching schemes. The
Euler flow was modeled as well as a Reynolds-averaged Navier Stokes
formulation was calculated. Two Euler cases were done using the Jameson,
MacCormack and the Shu schemes to advance in time. The computer code developed
at the UNC uses a Total Variation Diminishing (TVD) scheme implemented in a
non structured finite volume formulation for solving the 3D Euler equations
is presented. Finally the pressure coefficient distribution along the airfoil
chord and the contours of the flow properties were compared with other data
available in literature.
