The Effect of Grid Topology and Flow Solver on Turbulence Model Closure Coeffcient Uncertainties for a Transonic Airfoil


The goal of this work was to determine the effect of grid topology and flow solver on the quantification of uncertainty and sensitivity of commonly used turbulence models in Reynolds-Averaged Navier-Stokes codes due to uncertainty in the values of closure coefficients, and to rank the contribution of each coefficient to uncertainty in various output flow quantities of interest for the RAE 2822 transonic airfoil. Three turbulence models were considered: the Spalart-Allmaras Model, Wilcox (2006) k-ω Model, and the Menter Shear-Stress Transport Model. Several structured and unstructured grid topologies were employed in the analysis. The Fun3D code, developed by NASA Langley Research Center, and the BCFD code, developed by The Boeing Company, were used as the flow solvers. The uncertainty quantification analysis employed stochastic expansions based on non-intrusive polynomial chaos as an efficient means of uncertainty propagation. Sobol indices were used to rank the relative contributions of each closure coefficient to the total uncertainty in the output flow quantities of interest. The results of this study are in good agreement with previously published results.

Meeting Name

46th AIAA Fluid Dynamics Conference (2016: Jun. 13-17, Washington, DC)


Mechanical and Aerospace Engineering

Research Center/Lab(s)

Center for High Performance Computing Research

Keywords and Phrases

Airfoils; Codes (Symbols); Flow Simulation; Fluid Dynamics; NASA; Navier Stokes Equations; Shear Stress; Stochastic Systems; Supersonic Aircraft; Topology; Transonic Aerodynamics; Turbulence Models; NASA Langley Research Center; Relative Contribution; Reynolds Averaged Navier Stokes Codes; Shear-Stress Transport; Spalart-Allmaras Model; Total Uncertainties; Uncertainty Propagation; Uncertainty Quantifications; Uncertainty Analysis

International Standard Book Number (ISBN)


Document Type

Article - Conference proceedings

Document Version


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© 2016 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

Publication Date

01 Jun 2016

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