Impact of Turbulence Model Irregularity on High-Order Discretizations

A high-order, discontinuous Galerkin nite element discretization for the the Reynoldsaveraged Navier Stokes equations coupled with the Spalart-Allmaras turbulence model is presented and applied to subsonic airfoil test cases. In particular, grid renement studies are conducted to examine the accuracy of the scheme. The results of these renement studies demonstrate that optimal order of accuracy is not obtained. Adjoint based error estimates are used to investigate this loss of accuracy. The results demonstrate that the turbulent/non-turbulent interface at the boundary layer edge region, where the turbulence model solution is not smooth, contribute signicantly to the total error in the computed drag.

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