variavel0=<b>Ricardo Barbosa Damian</b> - damian@ciber.com.br UFRGS
<b>Antonio Batista de Jesus</b> - antonio.jesus@embraer.com.br EMBRAER
<b>Guilherme Lara Oliveira</b> - guilherme.oliveira@embraer.com.br EMBRAER
<b>Abstract.</b> The use of CFD commercial codes in the industry has became more common, particularly in the aeronautic. With the modeling and hardware evolution, it has been possible to accomplish more realistic simulations of the flow around airplanes. Actually aeronautic problem can be simulated using turbulent models, spatial grids and a number of computational cells of about 10^6. However when complex geometric and computational models are used it becomes very difficult to analyze local effects of the software on the analyzed flow due to the number of parameters involved. This work intents to compare two CFD commercial codes in some cases of simple flow with analytical solution known. Firstly, an inviscid, two-dimensional, flow around a cylinder was studied. The numeric obtained drag was calculated for compressible and incompressible conditions. Particularly, the influence of the number of grid points over the cylinder surface on the drag was studied. After, a one-dimensional shock tube was solved to evaluate the softwares performance on capturing discontinuities, comparing with the analytical solution. In each case, several possibilities offered by the codes were tested: interpolation order of the convective terms, coupled or segregated solvers, explicit or implicit time integration method.
<b>Keywords.</b> CFD, Inviscid Flow, Cylinder, Shock Tube, Validation.