Uncertainty Analysis of Turbulence Model Closure Coefficients for Shock Wave-Boundary Layer Interaction Simulations

Abstract

The purpose of this paper is to present results from an uncertainty and sensitivity analysis study of commonly used turbulence models in Reynolds-Averaged Navier-Stokes codes due to the epistemic uncertainty in closure Coefficients for shock wave-turbulent boundary layer interaction simulations. The study focuses on the analysis of an Axisymmetric Shock Wave Boundary Layer Interaction (ASWBLI) turbulence model validation case including an axisymmetric cylindrical body with a trailing edge flare of 20 degrees at an upstream Mach number of 7.11. The Spalart-Allmaras, the Wilcox (2006) κ-ω, and the Menter Shear-Stress Transport turbulence models are considered in the stochastic analyses of the ASWBLI, which utilized the FUN3. D flow solver from NASA Langley Research Center. The uncertainty quantification approach involves stochastic expansions based on non-intrusive polynomial chaos to efficiently propagate the uncertainty. Sensitivity analysis is performed with Sobol indices to rank the relative contribution of each closure Coefficient to the total uncertainty for several output flow quantities. The results of the current study identify a set of closure Coefficients which contribute most to the uncertainty in various output quantities of interest, which are also consistent with the findings of previous studies focusing on low-speed attached and separated flows and transonic wall-bounded flows including shock induced separation.

Meeting Name

AIAA Aerospace Sciences Meeting, 2018 (2018: Jan. 8-12, Kissimmee, FL)

Department(s)

Mechanical and Aerospace Engineering

Research Center/Lab(s)

Center for High Performance Computing Research

Comments

The authors would like to acknowledge the support for this research provided by the NASA Grant NNX14AN17A (technical monitor: Mujeeb Malik).

Keywords and Phrases

Atmospheric thermodynamics; Aviation; Boundary layer flow; Boundary layers; Hypersonic flow; NASA; Navier Stokes equations; Reynolds equation; Sensitivity analysis; Shear stress; Shock waves; Stochastic models; Stochastic systems; Supersonic aircraft; Turbulence models; Turbulent flow, NASA Langley Research Center; Quantities of interests; Reynolds averaged navier stokes codes; Shock induced separation; Shock wave boundary layer interactions; Turbulent boundary-layer interactions; Uncertainty and sensitivity analysis; Uncertainty quantifications, Uncertainty analysis

International Standard Book Number (ISBN)

978-162410524-1

Document Type

Article - Conference proceedings

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 2018 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

Publication Date

01 Jan 2018

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