Merge pull request #95 from sun5k/master

Flat Plates(T3A and T3A-) VandV and Tutorial for LM model

Author: sun5k

_tutorials/compressible_flow/Transitional_Flat_Plate/Transitional_Flat_Plate_T3A_and_T3A-.md

@@ -0,0 +1,113 @@
+---
+title: Transitional Flat Plate for T3A and T3A-
+permalink: /tutorials/Transitional_Flat_Plate/
+written_by: Sunoh Kang
+for_version: 7.4.0
+revised_by: -
+revision_date: -
+revised_version: -
+solver: RANS
+requires: SU2_CFD
+complexity: basic
+follows: 
+---
+
+## 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 & T3A-[ERCOFTAC](http://cfd.mace.manchester.ac.uk/ercoftac/doku.php). The following capabilities of SU2 will be showcased in this tutorial:
+
+- Steady, 2D, incompressible RANS equations
+- k-w SST-2003m turbulence model with Langtry and Menter 2009 ([LM2009](https://turbmodels.larc.nasa.gov/langtrymenter_4eqn.html)) transition model
+- L2Roe convective scheme in space (2nd-order, upwind)
+- Corrected average-of-gradients viscous scheme
+- Euler implicit time integration
+- farfield, Outlet, Symmetry and No-Slip Wall boundary conditions
+
+## Resources
+
+The resources for this tutorial can be found in the [compressible_flow/Transitional_Flat_Plate/LM](https://github.com/su2code/Tutorials/tree/master/compressible_flow/Transitional_Flat_Plate/LM) directory in the [tutorial repository](https://github.com/su2code/Tutorials). 
+
+## 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](/docs_v7/Download/) and [Installation](/docs_v7/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](https://turbmodels.larc.nasa.gov/langtrymenter_4eqn.html)) that uses k-w SST-2003m 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](http://cfd.mace.manchester.ac.uk/ercoftac/doku.php). 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 no-slip 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/10.2514/6.2022-3679.
+
+### Mesh Description
+
+The mesh used for T3A tutorial, which provided by [AIAA Transition modeling workshop-I](https://transitionmodeling.larc.nasa.gov).
+The mesh used for T3A- tutorial, which consists of 122,880 quadrilaterals.
+Both T3A and T3A- boundary conditions are shown below.
+
+![Flat Plate](../../../tutorials_files/compressible_flow/Transitional_Flat_Plate/images/LM_flat_plate/Boundary_conditions.png)
+
+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
+
+...
+
+%
+% Free-stream 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:
+
+1.	Copy the ([config file](https://github.com/su2code/Tutorials/tree/master/compressible_flow/Transitional_Flat_Plate/LM/)) and ([mesh file](https://github.com/su2code/Tutorials/tree/master/compressible_flow/Transitional_Flat_Plate/LM/)) 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.
+
+2.	Run the executable by entering 
+
+    ```
+    $ SU2_CFD transitional_LM_model_ConfigFile.cfg
+    ``` 
+
+    at the command line.
+
+3.	SU2 will print residual updates for each iteration of the flow solver, and the simulation will finish upon reaching the specified convergence criteria.
+
+4.	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. 
+
+![T3A_Cf_Rex](../../../tutorials_files/compressible_flow/Transitional_Flat_Plate/images/LM_flat_plate/Cf_T3A.png)
+Figure (2): Comparison of the skin friction coefficients for the T3A case.
+![T3A-_Cf_Rex](../../../tutorials_files/compressible_flow/Transitional_Flat_Plate/images/LM_flat_plate/Cf_T3A-.png)
+Figure (3): Comparison of the skin friction coefficients for the T3A- case.
+
+
+## Notes
+
+The [LM model](https://turbmodels.larc.nasa.gov/langtrymenter_4eqn.html) is designed using general subsonic transition experiment results(T-S wave, bypass transition, and separation-induced transition). So, This LM model can't provide appropriate simulation results for crossflow, supersonic, and hypersonic flow transition(= crossflow instability, 1st mode, Mack 2nd mode).

_tutorials/index.md

@@ -38,8 +38,10 @@ Simulation of external, laminar flow over a flat plate (classical Navier-Stokes
 Simulation of external, laminar flow around a 2D cylinder.
 * [Turbulent Flat Plate](/tutorials/Turbulent_Flat_Plate/)    
 Simulation of external, turbulent flow over a flat plate (classical RANS validation).
-* [Transitional Flat Plate](/tutorials/Transitional_Flat_Plate/)    
+* [Transitional Flat Plate(BC transition model)](/tutorials/Transitional_Flat_Plate/)    
 Simulation of external, transitional flow over a flat plate (transitional latminar-turbulent case).
+* [Transitional Flat Plate(LM transition model)](/tutorials/Transitional_Flat_Plate/)    
+Simulation of external, transitional flow over a flat plate(T3A & T3A-) (transitional latminar-turbulent case).
 * [Turbulent ONERAM6](/tutorials/Turbulent_ONERAM6/)     
 Simulation of external, viscous flow around a 3D geometry (isolated wing) using a turbulence model.
 * [Unsteady NACA0012](/tutorials/Unsteady_NACA0012/)     

_vandv/LM_transition.md

@@ -0,0 +1,137 @@
+---
+title: Langtry and Menter transition model
+permalink: /vandv/LM_transition/
+---
+
+| Solver | Version | Author |
+| --- | --- | --- |
+| `RANS` | 7.4.0 | S. Kang |
+
+The details of the Langtry and Menter(LM) transition model validation cases are taken from the [AIAA Transition modeling workshop-I](https://transitionmodeling.larc.nasa.gov).
+To validate the LM model, the simulation results of SU2 are compared with the results of Fluent19.0 with a similar numerical setting.
+
+## Problem Setup
+
+
+Flow conditions are the reference from : https://doi.org/10.2514/6.2022-3679 and [AIAA Transition modeling workshop-I](https://transitionmodeling.larc.nasa.gov).
+
+| Case | T3A | T3B | T3Am | NLF0416|
+| --- | --- | --- | --- | --- |
+|Inlet Velocity (m/s)| 69.44 | 69.44 | 19.8 | 34.72 |
+|Density (kg/m^3) | 0.053 | 0.053 | 1.2 | 2.13 |
+|Viscosity (kg/ms) | 1.85E-5 | 1.85E-5 | 1.79E-5 | Sutherland's Law |
+|Freestream Temperature (K) | 300 | 300 | 300 | 300 |
+|Unit Reynolds number (1/m) | 2.0E5 | 2.0E5 | 1.328E6 | 4.0E6 | 
+|Mach Number | 0.2 | 0.2 | 0.058 | 0.1 |
+|AoA | 0.0 | 0.0 | 0.0 | 0.0 |
+|Viscosity Ratio| 11.9 | 99.0 | 9.0 | 1.0 |
+|Freestream Turbulence Intensity (%) | 5.855 | 7.216 | 1.0 | 0.15 |
+
+
+## Mesh Description
+
+The grids of T3A, T3B, and NLF cases are provided by [TMW](https://transitionmodeling.larc.nasa.gov/workshop_i/)(Transition Model Workshop). And, The grid of T3Am was made with reference to https://doi.org/10.2514/6.2022-3679.
+If you want to run the above cases, you can use only the fine-level grid files available in the [SU2 V&V repository](https://github.com/su2code/Tutorials/tree/master/compressible_flow/Transitional_Flat_Plate/).
+
+
+## Numerical Scheme 
+
+| Flat plate | Fluent | SU2 |
+| --- | --- | --- |
+| Flux | Roe-FDS | L2ROE |
+| Gradient | Least Squares Cell Based | WEIGHTED_LEAST_SQUARES |
+| Spatial Discretization Flow | Third-order MUSCL | MUSCL_FLOW |
+| Spatial Discretization Turbulence | Third-order MUSCL | MUSCL_YES |
+
+
+| NLF0416 | Fluent | SU2 |
+| --- | --- | --- |
+| Flux | Roe-FDS | L2ROE |
+| Gradient | Least Squares Cell Based | WEIGHTED_LEAST_SQUARES |
+| Spatial Discretization Flow | second-order Upwind | MUSCL_FLOW |
+| Spatial Discretization Turbulence | second-order Upwind | MUSCL_YES |
+
+## Results
+
+Present results of all grid resolutions and then plot the results of the fine-level grid separately. If you want to see other results of the gird level, you can see them at "vandv_files/LMmodel".
+All of the flat plate results(= attached flow) are in good agreement with the Fluent results. But, the Airfoil results have the oscillation near the separation region both Fluent and SU2. 
+
+
+
+### T3A 
+The experiment data from [here](http://cfd.mace.manchester.ac.uk/ercoftac/)
+
+C : Coarse
+
+M : Medium
+
+F : Fine
+
+X : Extra fine
+
+
+
+<p align="center">
+<img src="/vandv_files/LM_model/T3A/All_Cf.png" alt="All result comparsion of Cf distribution on T3A" />
+<img src="/vandv_files/LM_model/T3A/Fine_Cf.png" alt="Fine level result comparsion of Cf distribution on T3A" />
+
+### T3B
+The experiment data from [here](http://cfd.mace.manchester.ac.uk/ercoftac/)
+
+C : Coarse
+
+M : Medium
+
+F : Fine
+
+X : Extra fine
+
+
+<p align="center">
+<img src="/vandv_files/LM_model/T3B/All_Cf.png" alt="All result comparsion of Cf distribution on T3B" />
+<img src="/vandv_files/LM_model/T3B/Fine_Cf.png" alt="Fine level result comparsion of Cf distribution on T3B" />
+
+
+### T3Am
+The experiment data from [here](http://cfd.mace.manchester.ac.uk/ercoftac/)
+
+Mesh_1 : Tiny
+
+Mesh_2 : Coarse
+
+Mesh_3 : Medium
+
+Mesh_4 : Fine
+
+Mesh_5 : Extra Fine
+
+Mesh_6 : Ultra Fine
+
+<p align="center">
+<img src="/vandv_files/LM_model/T3Am/All_Cf.png" alt="All result comparsion of Cf distribution on T3Am" />
+<img src="/vandv_files/LM_model/T3Am/Mesh5_Cf.png" alt="Fine level result comparsion of Cf distribution on T3Am" />
+
+
+### NLF0416
+Fluent and SU2, the NLF-0416 airfoil results oscillate near the separation region. So, Here are shown only the fine-level grid results of every 1000 iterations and the instantaneous.
+
+C : Coarse
+
+M : Medium
+
+F : Fine
+
+Every 1000 iteration results : 
+
+<p align="center">
+<img src="/vandv_files/LM_model/NLF/Delta_1000_Fine_Cp.png" alt="Fine level result comparsion of Cp distribution on NLF-0416" />
+<img src="/vandv_files/LM_model/NLF/Delta_1000_Fine_Cf.png" alt="Fine level result comparsion of Cf distribution on NLF-0416" />
+
+
+Instantaneous result is :
+
+<p align="center">
+<img src="/vandv_files/LM_model/NLF/Inst_All_Cp.png" alt="Fine level result comparsion of Cp distribution on NLF-0416" />
+<img src="/vandv_files/LM_model/NLF/Inst_All_Cf.png" alt="Fine level result comparsion of Cf distribution on NLF-0416" />
+<img src="/vandv_files/LM_model/NLF/Inst_Fine_Cp.png" alt="Fine level result comparsion of Cp distribution on NLF-0416" />
+<img src="/vandv_files/LM_model/NLF/Inst_Fine_Cf.png" alt="Fine level result comparsion of Cf distribution on NLF-0416" />

_vandv/index.md

@@ -29,3 +29,5 @@ Code-to-code comparisons for a bump in a channel, which results in pressure grad
 Results for the 30p30n airfoil, mesh independence study at low angle-of-attack, and determination of maximum lift, both comparing different numerical schemes.
 * [Shock-Wave Boundary-Layer Interaction](/vandv/swbli/)
 Comparison of grid-converged results with experimental data. SA and SST turbulence models.
+* [2D Flat Plate (T3A & T3A-) for Langtry and Menter transition model](/vandv/LM_transition/)
+Comparison of grid-converged results with results of another solver and experimental data.