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Transitional Flat Plate for T3A and T3A
Written by  for Version  Revised by  Revision date  Revised version 

@Sunoh Kang  7.5.0  @ 
Solver: 

Uses: 

Prerequisites: 
None 
Complexity: 
Basic 
Goals
Upon completing this tutorial, the user will be familiar with performing an external, transitional flow over a flat plate. The flow over the flat plate will be laminar until it reaches a point where a transition correlation depending on local flow variables is activated. The results can be compared to the zero pressure gradient natural transition experiment of T3A & T3AERCOFTAC. The following capabilities of SU2 will be showcased in this tutorial:
 Steady, 2D, incompressible RANS equations
 kw SST2003m turbulence model with Langtry and Menter 2009 (LM2009) transition model
 L2Roe convective scheme in space (2ndorder, upwind)
 Corrected averageofgradients viscous scheme
 Euler implicit time integration
 farfield, Outlet, Symmetry and NoSlip Wall boundary conditions
Resources
The resources for this tutorial can be found in the compressible_flow/Transitional_Flat_Plate/LM directory in the tutorial repository.
Tutorial
The following tutorial will walk you through the steps required when solving for the transitional flow over a flat plate using SU2. It is assumed you have already obtained and compiled the SU2_CFD code for a serial or parallel computation. If you have yet to complete these requirements, please see the Download and Installation pages.
Background
Practically, most CFD analyses are carried out using fully turbulent fields that do not account for boundary layer transition. Given that the flow is everywhere turbulent, no separation bubbles or other complex flow phenomena evolve. A transition model can be introduced, however, such that the flow begins as laminar by damping the production term of the turbulence model until a point where a transition correlation is activated. Currently, Langtry and Menter transition model (LM) that uses kw SST2003m as the baseline turbulence model is implemented in SU2.
For verification, we will be comparing SU2 results against the results of natural transition flat plate experiment of ERCOFTAC. The experimental data include skin friction coefficient distribution versus the local Reynolds number over the flat plate.
Problem Setup
The length of the flat plate is 20 meters, and it is represented by an adiabatic noslip wall boundary condition. There is a symmetry plane located before the leading edge of the flat plate. far boundary condition is used on the left and top boundary of the domain, and outlet boundary condition is applied to the right boundaries of the domain. Flow condition, you can reference from https://doi.org/10.2514/6.20223679.
Mesh Description
The mesh used for T3A tutorial, which provided by AIAA Transition modeling workshopI. The mesh used for T3A tutorial, which consists of 122,880 quadrilaterals. Both T3A and T3A boundary conditions are shown below.
Figure (1): Mesh with boundary conditions (red: far, blue:out, orange:symmetry, green:wall)
Configuration File Options
Several of the key configuration file options for this simulation are highlighted here.
% Physical governing equations (EULER, NAVIER_STOKES,
% WAVE_EQUATION, HEAT_EQUATION,
% LINEAR_ELASTICITY, POISSON_EQUATION)
SOLVER= RANS
%
% Specify turbulent model (NONE, SA, SST)
KIND_TURB_MODEL= SST
%
% Specify versions/corrections of the SST model (V2003m, V1994m, VORTICITY, KATO_LAUNDER, UQ, SUSTAINING)
SST_OPTIONS= NONE
%
% Transition model (NONE, LM)
KIND_TRANS_MODEL= LM
...
%
% Freestream turbulence intensity
FREESTREAM_TURBULENCEINTENSITY = 0.01
In the LM model, transition onset location is affected by freestream turbulence intensity.
Running SU2
To run this test case, follow these steps at a terminal command line:

Copy the (config file) and (mesh file) so that they are in the same directory. Move to the directory containing the config file and the mesh file. Make sure that the SU2 tools were compiled, installed, and that their install location was added to your path.

Run the executable by entering
$ SU2_CFD transitional_LM_model_ConfigFile.cfg
at the command line.

SU2 will print residual updates for each iteration of the flow solver, and the simulation will finish upon reaching the specified convergence criteria.

Files containing the results will be written upon exiting SU2. The flow solution can be visualized in Tecplot or ParaView.
Results
The figure below compares the skin friction results obtained by the LM transition model to the result of another solver(=Fluent 19.0) and experimental data.
Figure (2): Comparison of the skin friction coefficients for the T3A case. Figure (3): Comparison of the skin friction coefficients for the T3A case.
Notes
The LM model is designed using general subsonic transition experiment results(TS wave, bypass transition, and separationinduced transition). So, This LM model canâ€™t provide appropriate simulation results for crossflow, supersonic, and hypersonic flow transition(= crossflow instability, 1st mode, Mack 2nd mode).
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