2D T3A Flat Plate Verification

The purpose here is to provide a large sequence of nested grids of the same family, along with results from existing CFD codes that employ specific forms of particular turbulence models, in order to help programmers verify their implementations of these same models. On a given grid, there may be differences between the results from different codes, but presumably as the grid is refined the results should approach the same answer (if the flow conditions and boundary conditions are the same). With verification, the purpose is not to establish the "goodness" of a model compared to experiment, but rather to establish that a model has been implemented correctly, as intended according to the equations and boundary conditions. (It is through validation that a model's "goodness" is established.) The purpose here is primarily verification.

This test case corresponds to the T3A condition from the T3 series of test cases hosted by the ERCOFTAC (European Research Community on Flow, Turbulence, and Combustion). This case is run with the following flow conditions:

Inlet velocity (m/s)	69.44
Density (kg/m³)	0.053
Unit Reynolds Number (/m)	2.00E5
μ ∙ 10^-5 (kg/[m∙s])	1.85
Freestream temperature (K)	300.0
Mach number	0.200
μ_t/μ at inlet	11.90
Tu (%) at inlet	5.855
Tu (%) at the leading edge	3.300
Distance from inflow to plate leading edge (m)	0.250

The computational meshes for this case are those used in the following reference: Venkatachari, B. S., Mysore, P., V., Hildebrand, N., Choudhari, M., M., and Denison, M., F., Verification of the γ-Reθt Transition Model in OVERFLOW and FUN3D, Journal of Aircraft 2024 Vo. 61 No. 2, pp. 345-364, https://doi.org/10.2514/1.C037445. While the freestream Mach number of 0.2 is low enough that the flow is nearly incompressible, this is a compressible verification case. Therefore, incompressible codes would be expected to produce results that are close- but not quite the same- as the compressible solution for the refined grid. A visualization of the level 1 (most coarse) mesh used for this test case is shown below.

Responsible NASA Official: Ethan Vogel
Page Curator: Clark Pederson
Last Updated: 4/7/2025

RESULTS	LINK TO EQUATIONS	MRR Level
SST-2003-LM2009	SST-2003-LM2009 Equations	2

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