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Products developed at industries, institutes and research centers are expected to have high level of quality and performance, having a minimum waste, which require efficient and robust tools to numerically simulate stringent project conditions with great reliability. In this context, Computational Fluid Dynamics (CFD) plays an important role and the present work shows two numerical algorithms that are used in the CFD community to solve the Euler equations applied to typical aerospace and aeronautical problems. Particularly, unstructured discretization of the spatial domain has gained special attention by the international community due to its ease in discretizing complex spatial domains. This work has the main objective of illustrating some advantages and disadvantages of a centered algorithm and an upwind one using an unstructured spatial discretization of the flow governing equations. Numerical methods include a finite volume formulation and the Euler equations are applied to solve a supersonic flow over a ramp problem, a hypersonic flow over a blunt body problem, a hypersonic flow over a double ellipsoid problem and a supersonic flow over a simplified configuration of VLS problem. Convergence acceleration is obtained using a spatially variable time stepping procedure

Comparison between a centered and a flux difference split schemes using unstructured strategy