Bulletin of the American Physical Society
74th Annual Meeting of the APS Division of Fluid Dynamics
Volume 66, Number 17
Sunday–Tuesday, November 21–23, 2021; Phoenix Convention Center, Phoenix, Arizona
Session M08: Boundary Layers: Turbulent Boundary Layers II
1:10 PM–3:20 PM,
Monday, November 22, 2021
Room: North 123
Chair: Adrian Lozano-Duran, MIT
Abstract: M08.00006 : Reduced-order Modeling of Laminar Boundary Layers*
2:15 PM–2:28 PM
Presenter:
Carlos A Gonzalez
(Center for Turbulence Research, Stanford University)
Authors:
Carlos A Gonzalez
(Center for Turbulence Research, Stanford University)
Michael Karp
(Technion - Israel Institute of Technology)
Shaun R Harris
(Center for Turbulence Research, Stanford University)
Parviz Moin
(Center for Turbulence Research, Stanford University)
in the laminar and transitional region can be greater than that of the turbulent region by up to two
orders of magnitude in a wall-modeled large-eddy simulation (WMLES) (Slotnick, et al., 2014). The high
computational cost of this region is a barrier to the application of WMLES to transitional flows of
engineering interest, such as the flow near the leading edge of wings. Prior work (Gonzalez, et al., 2020)
implemented a reduced order model for laminar boundary layers based on the Falkner-Skan similarity
solution. This model was then tested in stagnation flow and a spatially varying pressure gradient
boundary layer and the results were in good agreement with the Navier Stokes solutions. In this
investigation, we present a further assessment of the model when applied to a NACA0012 airfoil. We
evaluate the accuracy of engineering quantities of interest, such as wall-stress, lift, and drag. In addition,
the model is integrated with the parabolized stability equations in order to identify the onset of
transition.
*Supported by NASA
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