added verification cases

_data/vandv.yml

@@ -9,3 +9,7 @@
   - FVM_Incomp_Navier_Stokes
   - FVM_Navier_Stokes
 
+- title: Verification Cases
+  vandv:
+  - Bump_Channel
+  - Flat_Plate

_vandv/verification/Bump_Channel.md

@@ -0,0 +1,79 @@
+---
+title: 2D Bump-in-Channel Verification Case
+permalink: /vandv/Bump_Channel/
+---
+
+<p align="center">
+<img src="/vandv_files/Bump_Channel/images/bump_cf_0p75_gridconv_sst.png" alt="Skin Friction Grid Convergence SST x = 0.75" width="435"/>
+</p>
+
+
+The details of the 2D Bump-in-Channel Verification case are taken from the [NASA TMR website](https://turbmodels.larc.nasa.gov/bump.html). 
+
+By comparing the SU2 results of the bump-in-channel case against CFL3D and FUN3D on a sequence of refined grids and seeing agreement of key quantities, we can build a high degree of confidence that the SA and SST models are implemented correctly. Therefore, the goal of this case is to verify the implementations of the SA and SST models in SU2.
+
+## Problem Setup
+
+The bump-in-channel case is low Mach test case (nearly incompressible) for a fully turbulent flow over a no-slip wall featuring an elevated bump on the surface. The primary difference between this case and the flat plate case is that pressure gradients are induced by the wall curvature of the bump, which makes this case more challenging for turbulence models.
+
+This problem will solve the flow past the bump with these conditions:
+- Freestream Temperature = 300 K
+- Freestream Mach number = 0.2
+- Reynolds number = 3.0E6
+- Reynolds length = 1.0 m
+
+The length of the section of wall with the bump is 1.5 meters, and it is represented by an adiabatic no-slip wall boundary condition. The lower boundaries of the domain upstream and downstream of the bump section are modeled as symmetry planes. Inlet and outlet boundary conditions are used on the left and right boundaries of the domain, and a symmetry boundary condition is used over the top region of the domain (the upper wall of the channel), which is located 5 meters away from the bump. All other fluid and boundary conditions are applied as prescribed on the NASA TMR website.
+
+## Mesh Description
+
+Structured meshes of increasing density are used to perform a grid convergence study. The meshes are identical to the 2D versions found on the [NASA TMR website](https://turbmodels.larc.nasa.gov/bump_grids.html) for this case after converting to 2D, unstructured CGNS format (ADF). These meshes are named according to the number of vertices in the x and y directions, respectively. The mesh sizes are: 
+
+1. 89x41  - 3520 quadrilaterals
+2. 177x81  - 14080 quadrilaterals
+3. 353x161 - 56320 quadrilaterals
+4. 705x321 - 225280 quadrilaterals
+5. 1409x641 - 901120 quadrilaterals
+
+![Turb Plate Mesh](/vandv_files/Bump_Channel/images/turb_plate_mesh_bcs.png)
+Figure (1): Mesh with boundary conditions: inlet (red), outlet (blue), far-field (orange), symmetry (purple), wall (green).
+
+If you would like to run the bump-in-channel problem for yourself, you can use the files available in the [SU2 V&V repository](https://github.com/su2code/VandV/tree/master/rans/bump_in_channel_2d). Configuration files for both the SA and SST cases, as well as all grids in CGNS format, are provided. A Python script is also distributed in order to easily recreate the figures seen below from the data. *Please note that the mesh files found in the repository have been gzipped to reduce storage requirements and should be unzipped before use.*
+
+## Results
+
+The results for the mesh refinement study are presented and compared to results from FUN3D and CFL3D, including results for both the SA and SST turbulence models.
+
+We will compare the convergence of the lift and drag coefficient on the bump with grid refinement, as well as the value of the skin friction coefficient at 3 locations on the bump (x = 0.63, x = 0.75, x = 0.87). We also show the skin friction and pressure coefficients plotted along the length of the bump. For both turbulence models, we present profiles of the eddy viscosity and x-velocity at the x = 0.75 location (top of the bump). For the SST model, we show additional profiles for the turbulent kinetic energy and dissipation near the wall at the x = 0.75 location. All cases were converged until the density residual was reduced to 10<sup>-13</sup>, which is demonstrated by a figure containing residual convergence histories for each mesh.
+
+Both the SA and SST models exhibit excellent agreement in the figures below. With grid refinement, we see that all quantities of interest asymptote very close to those of FUN3D and CFL3D (and additional codes not shown here but displayed on the NASA TMR), which builds high confidence in the implementations of these two turbulence models in SU2. The SU2 results for all profile comparisons are nearly indistinguishable from the CFL3D and FUN3D counterparts.
+
+### SA Model
+
+<p align="center">
+<img src="/vandv_files/Bump_Channel/images/bump_cd_gridconv_sa.png" alt="Drag Grid Convergence SA" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cl_gridconv_sa.png" alt="Lift Grid Convergence SA" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cf_0p63_gridconv_sa.png" alt="Skin Friction Grid Convergence SA x = 0.63" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cf_0p75_gridconv_sa.png" alt="Skin Friction Grid Convergence SA x = 0.75" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cf_0p87_gridconv_sa.png" alt="Skin Friction Grid Convergence SA x = 0.87" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cf_profile_sa.png" alt="Skin Friction Profile SA" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cp_profile_sa.png" alt="Pressure Profile SA" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_eddy_profile_sa.png" alt="Eddy Viscosity Profile SA" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_vel_profile_sa.png" alt="Velocity Profile SA" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_residual_convergence_sa.png" alt="Residual Convergence SA" width="435"/>
+</p>
+
+### SST Model
+
+<p align="center">
+<img src="/vandv_files/Bump_Channel/images/bump_cd_gridconv_sst.png" alt="Drag Grid Convergence SST" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cl_gridconv_sst.png" alt="Lift Grid Convergence SST" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cf_0p63_gridconv_sst.png" alt="Skin Friction Grid Convergence SST x = 0.63" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cf_0p75_gridconv_sst.png" alt="Skin Friction Grid Convergence SST x = 0.75" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cf_0p87_gridconv_sst.png" alt="Skin Friction Grid Convergence SST x = 0.87" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cf_profile_sst.png" alt="Skin Friction Profile SST" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_cp_profile_sst.png" alt="Pressure Profile SST" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_eddy_profile_sst.png" alt="Eddy Viscosity Profile SST" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_vel_profile_sst.png" alt="Velocity Profile SST" width="435"/>
+<img src="/vandv_files/Bump_Channel/images/bump_residual_convergence_sst.png" alt="Residual Convergence SST" width="435"/>
+</p>
+

_vandv/verification/Flat_Plate.md

@@ -0,0 +1,66 @@
+---
+title: Zero Pressure Gradient Flat Plate
+permalink: /vandv/Flat_Plate/
+---
+
+
+<p align="center">
+<img src="/vandv_files/Flat_Plate/images/flatplate_cd_gridconv_sa.png" alt="Drag Grid Convergence SA" width="435"/>
+</p>
+
+The details of the Zero Pressure Gradient Flat Plate case are taken from the [NASA TMR website](https://turbmodels.larc.nasa.gov/flatplate.html).
+
+By comparing the SU2 results of the flat plate case against CFL3D and FUN3D on a sequence of refined grids and seeing agreement of key quantities, we can build a high degree of confidence that the SA and SST models are implemented correctly. Therefore, the goal of this case is to verify the implementations of the SA and SST models in SU2.
+
+## Problem Setup
+
+Turbulent flow over a zero pressure gradient flat plate is a common test case for the verification of turbulence models in CFD solvers. The flow is everywhere turbulent and a boundary layer develops over the surface of the flat plate. The lack of separation or other more complex flow phenomena allows turbulence models to predict the flow with a high level of accuracy.
+
+This problem will solve the flow past the flatplate with these conditions:
+- Freestream Temperature = 300 K
+- Freestream Mach number = 0.2
+- Reynolds number = 5.0E6
+- Reynolds length = 1.0 m
+
+The length of the flat plate is 2 meters, and it is represented by an adiabatic no-slip wall boundary condition. Also part of the domain is a symmetry plane located before the leading edge of the flat plate. Inlet and outlet boundary conditions are used on the left and right boundaries of the domain, and a far-field boundary condition is used over the top region of the domain, which is located 1 meter away from the flat plate. All other fluid and boundary conditions are applied as prescribed on the NASA TMR website.
+
+## Mesh Description
+
+Structured meshes of increasing density are used to perform a grid convergence study. The meshes are identical to the 2D versions found on the [NASA TMR website](https://turbmodels.larc.nasa.gov/flatplate_grids.html) for this case after converting to native SU2 ASCII mesh format. These meshes are named according to the number of vertices in the x and y directions, respectively. The mesh sizes are:
+
+1. 35x25   - 816 quadrilaterals
+2. 69x49   - 3264 quadrilaterals
+3. 137x97  - 13056 quadrilaterals
+4. 273x193 - 52224 quadrilaterals
+5. 545x385 - 208896 quadrilaterals
+
+![Turb Plate Mesh](/vandv_files/Flat_Plate/images/turb_plate_mesh_bcs.png)
+Figure (1): Mesh with boundary conditions: inlet (red), outlet (blue), far-field (orange), symmetry (purple), wall (green).
+
+If you would like to run the flat plate problems for yourself, you can use the files available in the [SU2 V&V repository](https://github.com/su2code/VandV/tree/master/rans/flatplate). Configuration files for both the SA and SST cases, as well as all grids in SU2 format, are provided. A Python script is also distributed in order to easily recreate the figures seen below from the data.
+
+## Results
+
+The results for the mesh refinement study are presented and compared to results from FUN3D and CFL3D, including results for both the SA and SST turbulence models.
+
+We will compare the convergence of the drag coefficient on the flat plate with grid refinement, as well as the value of the skin friction coefficient at one point on the plate (x = 0.97). We also show the skin friction coefficient plotted along the length of the plate. All cases were converged until the density residual was reduced to 10<sup>-13</sup>, which is demonstrated by a figure containing residual convergence histories for each mesh.
+
+Both the SA and SST models exhibit excellent agreement in the figures below. With grid refinement, we see that both drag and skin friction values asymptote very close to those of FUN3D and CFL3D (and additional codes not shown here but displayed on the NASA TMR), which builds high confidence in the implementations of these two turbulence models in SU2.
+
+### SA Model
+
+<p align="center">
+<img src="/vandv_files/Flat_Plate/images/flatplate_cd_gridconv_sa.png" alt="Drag Grid Convergence SA" width="435"/>
+<img src="/vandv_files/Flat_Plate/images/flatplate_cf_0p97_gridconv_sa.png" alt="Skin Friction Grid Convergence SA" width="435"/>
+<img src="/vandv_files/Flat_Plate/images/flatplate_cf_profile_sa.png" alt="Skin Friction Profile SA" width="435"/>
+<img src="/vandv_files/Flat_Plate/images/flatplate_residual_convergence_sa.png" alt="Residual Convergence SA" width="435"/>
+</p>
+
+### SST Model
+
+<p align="center">
+<img src="/vandv_files/Flat_Plate/images/flatplate_cd_gridconv_sst.png" alt="Drag Grid Convergence SST" width="435"/>
+<img src="/vandv_files/Flat_Plate/images/flatplate_cf_0p97_gridconv_sst.png" alt="Skin Friction Grid Convergence SST" width="435"/>
+<img src="/vandv_files/Flat_Plate/images/flatplate_cf_profile_sst.png" alt="Skin Friction Profile SST" width="435"/>
+<img src="/vandv_files/Flat_Plate/images/flatplate_residual_convergence_sst.png" alt="Residual Convergence SST" width="435"/>
+</p>