TY - GEN
T1 - Application of Wray-Agarwal Turbulence Model for Flow past Joukowski Airfoil
T2 - AIAA SciTech Forum and Exposition, 2023
AU - Ryan-Simmons, Dean M.
AU - Agarwal, Ramesh K.
N1 - Publisher Copyright:
© 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2023
Y1 - 2023
N2 - Validation and verification benchmark test cases are employed in computation fluid dynamics (CFD) to determine the best practices in application of various CFD tools, namely the geometry modeling, mesh generation, numerical algorithms and turbulence models to ensure consistent and accurate numerical simulation of physical phenomena. In NASA’s High Fidelity CFD Workshop 2022, the Joukowski airfoil was identified as a benchmark case to test the convergence behavior of different turbulence models in different CFD solvers with particular emphasis on SA-neg-QCR 2000 turbulence model. This paper studies the accuracy and convergence behavior of Wray-Agarwal (WA) and Spalart-Allmaras (SA) one equation turbulence models by computing the flow past Joukowski airfoil on a sequence of seven workshop specified grids from coarse to fine. The benchmark case has free stream Mach number = 0.15, chord Reynolds number = 3x106 and angle of attack of 0 degree. The goal is to evaluate the convergence of drag coefficient on a sequence of five grids using WA and original version of SA model. CFD solver employed is ANSYS Fluent. Both models exhibit nearly first order convergence rates for first order solutions and second order convergence rates for second order solutions. There is no notable difference in the convergence rates between the two turbulence models for both first order and second order implementations.
AB - Validation and verification benchmark test cases are employed in computation fluid dynamics (CFD) to determine the best practices in application of various CFD tools, namely the geometry modeling, mesh generation, numerical algorithms and turbulence models to ensure consistent and accurate numerical simulation of physical phenomena. In NASA’s High Fidelity CFD Workshop 2022, the Joukowski airfoil was identified as a benchmark case to test the convergence behavior of different turbulence models in different CFD solvers with particular emphasis on SA-neg-QCR 2000 turbulence model. This paper studies the accuracy and convergence behavior of Wray-Agarwal (WA) and Spalart-Allmaras (SA) one equation turbulence models by computing the flow past Joukowski airfoil on a sequence of seven workshop specified grids from coarse to fine. The benchmark case has free stream Mach number = 0.15, chord Reynolds number = 3x106 and angle of attack of 0 degree. The goal is to evaluate the convergence of drag coefficient on a sequence of five grids using WA and original version of SA model. CFD solver employed is ANSYS Fluent. Both models exhibit nearly first order convergence rates for first order solutions and second order convergence rates for second order solutions. There is no notable difference in the convergence rates between the two turbulence models for both first order and second order implementations.
UR - http://www.scopus.com/inward/record.url?scp=85200143800&partnerID=8YFLogxK
U2 - 10.2514/6.2023-1613
DO - 10.2514/6.2023-1613
M3 - Conference contribution
AN - SCOPUS:85200143800
SN - 9781624106996
T3 - AIAA SciTech Forum and Exposition, 2023
BT - AIAA SciTech Forum and Exposition, 2023
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
Y2 - 23 January 2023 through 27 January 2023
ER -