Keywords and Phrases
Boundary Layer; CFD; Direct Numerical Simulations; Hypersonic; RANS; Reynolds Averaged Navier Stokes
“This study describes the use of Computational Fluid Dynamics (CFD) codes to simulate hypersonic boundary layers using several different turbulent closure models and comparing Reynolds-Averaged Navier-Stokes (RANS) simulations against Direct Numerical Simulations (DNS) of similar test cases. The test cases in this study consist of a flat plate in a Mach 8 freestream with a zero pressure gradient and wall recovery ratio of 0.48, as well as a Mach 8 axisymmetric nozzle also with a cold wall. The RANS models used in this study are the Spalart-Allmaras model, Baldwin-Lomax model, Menter K-Omega Baseline and Menter K-Omega Shear Stress Transport models. For verification purposes, two different CFD codes were used: NASA CFL3D version 6, and ANSYS Fluent 2019. It was found that in the flat plate case, all of the models matched fairly well with the DNS data in both codes. In the nozzle case, the Baldwin-Lomax, Splalart-Allmaras, and the K-Omega Shear Stress Transport models performed well, while the K-Omega Baseline model was not consistent between solvers. From the findings of this document, the recommended models for this use case are the Spalart-Allmaras and the k-m Shear Stress Transport models due to the robustness of the Spalart-Allmaras model and the accuracy of the k-m Shear Stress Transport model”--Abstract, page iii.
Isaac, Kakkattukuzhy M.
Duan, Lian, 1983-
Riggins, David W.
Mechanical and Aerospace Engineering
M.S. in Aerospace Engineering
Missouri University of Science and Technology
xiv, 89 pages
© 2020 Jorge-Valentino Kurose Bretzke, All rights reserved.
Thesis - Open Access
Electronic OCLC #
Bretzke, Jorge-Valentino Kurose, "Comparison of Reynolds-averaged Navier-Stokes turbulence models for simulating boundary layers in hypersonic flows" (2020). Masters Theses. 7962.