Langtry and Menter transition model

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. 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.

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(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. If you want to run the E387 test case you can use the mesh file available in the SU2 V&V repository

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

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


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