Finite Volume Simulation Of A Flow Over A Naca 0012 Using Jameson, Maccormack, Shu And Tvd Esquemes.

Abstract

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.