Abstract
The numerical simulation of the compressible flow passed a NACA 0012 airfoil has been undertaken using the Naviers-Stokes and total energy equations. The resolution of the governing equations is based on a Roe’s approximate Riemann solver. The integration of these equations is performed by means of an implicit upwind Total Variation Diminishing (TVD) scheme, developed by Harten and Yee. The resolution of the set of the governing equations is based on an Alternating Direction Implicit (ADI) formulation. A description of the numerical integration of the equations is first given. The resolution of the governing equations is then described. Two configurations has been investigated. First, this numerical code was checked on the calculation of the compressible flow in the vicinity of a NACA 0012 airfoil without incidence. Secondly, the interaction between a vortex and a NACA 0012 airfoil has been investigated. In these two calculations, the Mach and Reynolds numbers are respectively equal to 0.6 and 22000., the CFL number is 20. The numerical results are reviewed. A quite good agreement with numerical results obtain by other authors on similar configuration has been obtained.
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