Comparison of CFD solvers for low speed vortex dominated flows

CFD computations on a supersonic aircraft configuration at low speed and high angle of attack have been performed using three different software packages with the aim of studying the capability of the code to simulate the flow and to check the solver dependency. The solvers used are ADCS, elsA, and TAU. A single hexahedral mesh is used throughout the study. Results show a good correlation between the solvers with some discrepancy in terms of vortical flow for the high angle of attack, high Reynolds number case.