A Unified Implicit CFD Approach for Turbulent Flow Aerospace Configuration Simulations

On the Influence of Gradient Reconstruction Procedures Over the Accuracy of Finite Volume Based Schemes

“…Consequently, only two procedures are yet to be established: the reconstruction scheme used for the evaluation of the face flux vectors, F k , as well as a procedure for integrating ∂ Q i ∂t over time. Here, Roe's second-order TVD scheme, coupled with Venkatakrishnan's limiter [8], is employed in the discretization of all inviscid fluxes [5,6], including the ones related to the turbulence model. The integration of the temporal derivatives is performed by using an implicit time-march scheme, as described in Refs.…”

“…The integration of the temporal derivatives is performed by using an implicit time-march scheme, as described in Refs. [5,6]. These schemes were chosen as part of an effort to improve the overall robustness of the solution process.…”

“…In the current work, the three-dimensional flow dynamics are modeled using the compressible Reynolds-averaged Navier-Stokes (RANS) equations [2]. These equations are discretized in a cellcentered FV framework by using Roe's flux-difference splitting scheme for the reconstruction of the convective fluxes [4,5,6]. A second-order, total-variation diminishing (TVD), version of the scheme is implemented by using a piece-wise linear reconstruction of the solution [7], coupled with Venkatakrishnan's limiter [8].…”

“…Simulations are performed using an in-house code, BRU3D [5,6], for three different cases. The first one is a two-dimensional turbulent flat plate [11], which is mainly used as a sanity test case.…”

“…Its main purpose is to observe the influence that the different procedures have over the value of the aerodynamic coefficients when a separation bubble is present in the solution. The final case is the transonic OAT15A airfoil [12,5,6]. It illustrates the performance of each scheme when a shock wave is present in the domain.…”