diff --git a/_docs_v7/Physical-Definition.md b/_docs_v7/Physical-Definition.md index 71830f70..7ef7520b 100644 --- a/_docs_v7/Physical-Definition.md +++ b/_docs_v7/Physical-Definition.md @@ -158,3 +158,25 @@ The following modifications are allowed: - Curvature corrections are currently not implemented. Modifications from each of these three groups can be combined, for example `SST_OPTIONS= V2003m, VORTICITY, SUSTAINING` + +## Transition Models ## + +| Solver | Version | +| --- | --- | +| `*_RANS` | 7.5.0 | + +This section describes how to setup transition models for RANS simulations. Transition is activated using the option `KIND_SOLVER= RANS`, or `KIND_SOLVER= INC_RANS` together with a choice of `KIND_TRANS_MODEL` (different from `NONE`). +Currently, the only valid option for `KIND_TRANS_MODEL` is `LM`, for Langtry-Menter transition models. +Different submodels and correlations are then specified via `LM_OPTIONS` (for example `LM_OPTIONS= LM2015, MENTER_LANGTRY`). + +The following modifications are allowed: +- Versions: + - `LM2015` - Correction to include stationary crossflow instabilities. It has to be used only in 3D problems. The RMS of roughness used in this model has to be set through the separate option `HROUGHNESS`. +- Correlations (only one can be specified): + - `MALAN` - This is the default correlation when the LM model is coupled with the `SA` turbulence model. + - `SULUKSNA` - This should be used only if the `SST` model is used. It should require a formulation of the Re_theta_t correlation that omits the pressure gradient parameter, however it is not clear. + - `KRAUSE` - This correlation should be used for hypersonic flows. Its implementation at the moment is unclear due to inconsistencies in the literature. + - `KRAUSE_HYPER` - This correlation should be used for hypersonic flows. Its implementation at the moment is unclear due to inconsistencies in the literature. + - `MEDIDA` - Designed for `SA` turbulence model. Has problems when dealing with separation induced transition. + - `MEDIDA_BAEDER` - Designed for `SA` turbulence model. Has problems when dealing with separation induced transition. + - `MENTER_LANGTRY` - This is the default correlation when the LM model is coupled with the `SST` turbulence model. diff --git a/_tutorials/compressible_flow/Transitional_Flat_Plate/Transitional_Flat_Plate_T3A_and_T3A-.md b/_tutorials/compressible_flow/Transitional_Flat_Plate/Transitional_Flat_Plate_T3A_and_T3A-.md new file mode 100644 index 00000000..9c75649d --- /dev/null +++ b/_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). diff --git a/_tutorials/index.md b/_tutorials/index.md index 97c05658..63d6c521 100644 --- a/_tutorials/index.md +++ b/_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/) diff --git a/_tutorials/multiphysics/Unsteady_FSI_Python/Dynamic_FSI_Python.md b/_tutorials/multiphysics/Unsteady_FSI_Python/Dynamic_FSI_Python.md index cbb30c02..2108c604 100644 --- a/_tutorials/multiphysics/Unsteady_FSI_Python/Dynamic_FSI_Python.md +++ b/_tutorials/multiphysics/Unsteady_FSI_Python/Dynamic_FSI_Python.md @@ -161,7 +161,6 @@ DEFORM_MESH = YES MARKER_DEFORM_MESH = ( airfoil ) DEFORM_STIFFNESS_TYPE = WALL_DISTANCE DEFORM_LINEAR_SOLVER_ITER= 200 -MARKER_FLUID_LOAD = ( airfoil ) ``` Where we selected the airfoil as our marker for coupling. diff --git a/_vandv/LM_transition.md b/_vandv/LM_transition.md new file mode 100644 index 00000000..79898df2 --- /dev/null +++ b/_vandv/LM_transition.md @@ -0,0 +1,181 @@ +--- +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 | E387| +| --- | --- | --- | --- | --- | --- | +|Inlet Velocity (m/s)| 69.44 | 69.44 | 19.8 | 34.72 | 20.42 | +|Density (kg/m^3) | 0.053 | 0.053 | 1.2 | 2.13 | 0.175 | +|Viscosity (kg/ms) | 1.85E-5 | 1.85E-5 | 1.79E-5 | Sutherland's Law | Sutherland's Law | +|Freestream Temperature (K) | 300 | 300 | 300 | 300 | 288.15 | +|Unit Reynolds number (1/m) | 2.0E5 | 2.0E5 | 1.328E6 | 4.0E6 | 2.0E5 | +|Mach Number | 0.2 | 0.2 | 0.058 | 0.1 | 0.06 | +|AoA | 0.0 | 0.0 | 0.0 | 0.0 | 0,2,4,6 | +|Viscosity Ratio| 11.9 | 99.0 | 9.0 | 1.0 | 1.0 | +|Freestream Turbulence Intensity (%) | 5.855 | 7.216 | 1.0 | 0.15 | 0.001 | +|Turbulence Problem | SST | SST | SST | SST | SA/SST | + + +## Mesh Description + +The grids of T3A, T3B, and NLF cases are provided by [TMW](https://transitionmodeling.larc.nasa.gov/workshop_i/)(Transition Model Workshop). The grid of T3Am was made with reference to https://doi.org/10.2514/6.2022-3679. At the moment, no mesh convergence study has been performed on E387 case. The grid of Eppler E387 was made with reference to https://doi.org/10.1177/0954406217743537. +If you want to run the above cases (Flat plate), 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/). If you want to run the E387 test case you can use the mesh file available in the [SU2 V&V repository](https://github.com/su2code/Tutorials/tree/master/compressible_flow/Transitional_Airfoil/) + + +## 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 | + +| E387 | SU2 | +| --- | --- | +| Flux | L2ROE/ROE | +| Gradient | WEIGHTED_LEAST_SQUARES | +| Spatial Discretization Flow | MUSCL_FLOW | +| Spatial Discretization Turbulence | UPWIND | + +## 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 grid 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 NLF0416 results have the oscillation near the separation region both Fluent and SU2. +All of the E387 results are in good agreement with respect to experimental results. Only the combination SST_v2003m-LM seems to predict early transition at higher angles of attack. + + + +### T3A +The experiment data from [here](http://cfd.mace.manchester.ac.uk/ercoftac/) + +C : Coarse + +M : Medium + +F : Fine + +X : Extra fine + + + +

+All result comparsion of Cf distribution on T3A +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 + + +

+All result comparsion of Cf distribution on T3B +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 + +

+All result comparsion of Cf distribution on T3Am +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 : + +

+Fine level result comparsion of Cp distribution on NLF-0416 +Fine level result comparsion of Cf distribution on NLF-0416 + + +Instantaneous result is : + +

+Fine level result comparsion of Cp distribution on NLF-0416 +Fine level result comparsion of Cf distribution on NLF-0416 +Fine level result comparsion of Cp distribution on NLF-0416 +Fine level result comparsion of Cf distribution on NLF-0416 + + +### E387 +Experimental results are available. The pressure coefficient distribution has been compared for 4 angles of attack, namely 0deg, 2deg, 4deg, and 6deg. Cl-alpha and polar curves are also avaliable for comparison. + +Pressure coefficient distribution obtained through ROE scheme. + +

+-Cp distribution for AoA = 0deg +-Cp distribution for AoA = 2deg +-Cp distribution for AoA = 4deg +-Cp distribution for AoA = 6deg + + +Cl-alpha and polar curve obtained through ROE scheme. + +

+Cl-alpha curve +Polar curve + + +Pressure coefficient distribution obtained through L2ROE scheme. + +

+-Cp distribution for AoA = 0deg +-Cp distribution for AoA = 2deg +-Cp distribution for AoA = 4deg +-Cp distribution for AoA = 6deg + + +Cl-alpha and polar curve obtained through L2ROE scheme. + +

+Cl-alpha curve +Polar curve \ No newline at end of file diff --git a/_vandv/index.md b/_vandv/index.md index 46c0705e..15ed7f9a 100644 --- a/_vandv/index.md +++ b/_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. diff --git a/tutorials_files/compressible_flow/Transitional_Flat_Plate/images/LM_flat_plate/Boundary_conditions.png b/tutorials_files/compressible_flow/Transitional_Flat_Plate/images/LM_flat_plate/Boundary_conditions.png new file mode 100644 index 00000000..a48fb974 Binary files /dev/null and b/tutorials_files/compressible_flow/Transitional_Flat_Plate/images/LM_flat_plate/Boundary_conditions.png differ diff --git a/tutorials_files/compressible_flow/Transitional_Flat_Plate/images/LM_flat_plate/Cf_T3A-.png b/tutorials_files/compressible_flow/Transitional_Flat_Plate/images/LM_flat_plate/Cf_T3A-.png new file mode 100644 index 00000000..7fb5f56e Binary files /dev/null and b/tutorials_files/compressible_flow/Transitional_Flat_Plate/images/LM_flat_plate/Cf_T3A-.png differ diff 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