  In the context of the cell centered finite volume approach, care must be
taken when performing the reconstruction of property gradients at cell
interfaces. The present work analyzes three different gradient reconstruction
procedures, using three different turbulent simulation test cases, namely the
zero-gradient flat plate, the subsonic NACA 0012 airfoil and the transonic
OAT15A airfoil. The analysis is concerned mainly with the usage of
quadrilateral meshes. The gas dynamics equations are solved using an implicit
implementation of Roe's second-order upwind scheme. The RANS closure problem is
solved by using the negative Spalart-Allmaras turbulence model. The solution
quality of each gradient discretization procedure is analyzed and compared to
experimental data and other numerical solutions available in the literature.
For the cases considered here, excellent agreement is obtained between the
computed solutions and the expected results, regardless of which gradient
reconstruction scheme is used.
