[haukne]

Hi everyone,

I’m a first time SU2 user for my undergrad research project. I’ve downloaded the current release for Windows 10 and followed the Windows Installation doc. I have successfully run the compressible Inviscid Bump in a Channel and Laminar Flat Plate tutorials, so I know that my setup is correct.

My issue arises when trying to run the incompressible Turbulent NACA 0012 tutorial (https://su2code.github.io/tutorials/...lent_NACA0012/), the one most relevant to my work. When attempting to run SU2_CFD in serial with the config file (turb_naca0012.cfg) as found on the repository, I get the following error:


Error in "void CConfig::SetConfig_Parsing(char*)":
-------------------------------------------------------------------------
INC_DENSITY_INIT: invalid option name. Check current SU2 options in config_template.cfg.
INC_VELOCITY_INIT: invalid option name. Check current SU2 options in config_template.cfg.
INC_NONDIM: invalid option name. Check current SU2 options in config_template.cfg.
INC_DENSITY_REF: invalid option name. Check current SU2 options in config_template.cfg.
INC_VELOCITY_REF: invalid option name. Check current SU2 options in config_template.cfg.
INC_TEMPERATURE_REF: invalid option name. Check current SU2 options in config_template.cfg.
CONV_NUM_METHOD_FLOW: improper option value for type convect

------------------------------ Error Exit -------------------------------

job aborted:
[ranks] message

[0] application aborted
aborting MPI_COMM_WORLD (comm=0x44000000), error 0, comm rank 0


I tried to comment out these variables in the config file to see if anything would change. When I do this, it looks like SU2 sets up the solver and does everything up to solving the problem:


-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 6.0.0 "Falcon" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| The current SU2 release has been coordinated by the |
| SU2 International Developers Society <www.su2devsociety.org> |
| with selected contributions from the open-source community. |
-------------------------------------------------------------------------
| The main research teams contributing to the current release are: |
| - Prof. Juan J. Alonso's group at Stanford University. |
| - Prof. Piero Colonna's group at Delft University of Technology. |
| - Prof. Nicolas R. Gauger's group at Kaiserslautern U. of Technology. |
| - Prof. Alberto Guardone's group at Polytechnic University of Milan. |
| - Prof. Rafael Palacios' group at Imperial College London. |
| - Prof. Vincent Terrapon's group at the University of Liege. |
| - Prof. Edwin van der Weide's group at the University of Twente. |
| - Lab. of New Concepts in Aeronautics at Tech. Inst. of Aeronautics. |
-------------------------------------------------------------------------
| Copyright 2012-2018, Francisco D. Palacios, Thomas D. Economon, |
| Tim Albring, and the SU2 contributors. |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------

------------------------ Physical Case Definition -----------------------
Incompressible RANS equations.
Turbulence model: Spalart Allmaras
Hybrid RANS/LES: No Hybrid RANS/LES
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0.25, 0, 0).
Surface(s) where the force coefficients are evaluated: airfoil.

Surface(s) plotted in the output file: airfoil.
Input mesh file name: n0012_897-257.su2

---------------------- Space Numerical Integration ----------------------
Scalar upwind solver for the turbulence model.
First order integration in space.
Average of gradients with correction (viscous flow terms).
Average of gradients with correction (viscous turbulence terms).
Gradient computation using Green-Gauss theorem.
Artificial compressibility factor: 1.

---------------------- Time Numerical Integration -----------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-010.
Max number of linear iterations: 10.
No CFL adaptation.
Courant-Friedrichs-Lewy number: 25
Euler implicit time integration for the turbulence model.

------------------------- Convergence Criteria --------------------------
Maximum number of iterations: 99999.
Reduce the density residual 12 orders of magnitude.
The minimum bound for the density residual is 10^(-14).
Start convergence criteria at iteration 10.

-------------------------- Output Information ---------------------------
Writing a flow solution every 250 iterations.
Writing the convergence history every 1 iterations.
The output file format is Paraview ASCII (.vtk).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown.dat.
Surface flow coefficients file name: surface_flow.
Flow variables file name: flow.
Restart flow file name: restart_flow.dat.

------------------- Config File Boundary Information --------------------
Far-field boundary marker(s): farfield.
Constant heat flux wall boundary marker(s): airfoil.

---------------------- Read Grid File Information -----------------------
Two dimensional problem.
230336 points.
2 surface markers.
512 boundary elements in index 0 (Marker = airfoil).
1408 boundary elements in index 1 (Marker = farfield).
229376 quadrilaterals.

------------------------- Geometry Preprocessing ------------------------
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of the LINE surface elements.
Identifying edges and vertices.
Computing centers of gravity.
Setting the control volume structure.
Area of the computational grid: 8.76e+005.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 1.96e+003. Mean K: 5.1. Standard deviation K: 46.7.
Checking for periodicity.
Computing wall distances.
Wetted area = 2.04 m.
Area projection in the x-plane = 0.119 m, y-plane = 1 m.
Max. coordinate in the x-direction = 1 m, y-direction = 0.0595 m.
Min coordinate in the x-direction = 0 m, y-direction = -0.0595 m,.

------------------------- Driver information --------------------------
A Fluid driver has been instantiated.

------------------------ Iteration Preprocessing ------------------------
Zone 1: Euler/Navier-Stokes/RANS fluid iteration.

------------------------- Solver Preprocessing --------------------------
Force coefficients computed using free-stream values.
Viscous and Inviscid flow: rho_ref, and vel_ref
are based on the free-stream values, p_ref = rho_ref*vel_ref^2.
The free-stream value of the pressure is 0.
Mach number: nan, computed using the Bulk modulus.
Angle of attack (deg): 0, computed using the the free-stream velocity.
Side slip angle (deg): 0, computed using the the free-stream velocity.
Reynolds number: 1, computed using free-stream values.
Only dimensional computation, the grid should be dimensional.
-- Input conditions:
Bulk modulus: 142000 Pa.
Artificial compressibility factor: 1 Pa.
Free-stream static pressure: 0 Pa.
Free-stream total pressure: nan Pa.
Free-stream density: -1 kg/m^3.
Free-stream velocity: (1, 0) m/s. Magnitude: 1 m/s.
Free-stream viscosity: -1 N.s/m^2.
Free-stream turb. kinetic energy per unit mass: 0.00375 m^2/s^2.
Free-stream specific dissipation: 0.000375 1/s.
-- Reference values:
Reference pressure: -1 Pa.
Reference density: -1 kg/m^3.
Reference velocity: 1 m/s.
Reference length: 1 m.
Reference viscosity: -1 N.s/m^2.
-- Resulting non-dimensional state:
Mach number (non-dim): nan
Reynolds number (non-dim): 1. Re length: 1 m.
Free-stream pressure (non-dim): 0
Free-stream density (non-dim): 1
Free-stream velocity (non-dim): (1, 0). Magnitude: 1
Free-stream viscosity (non-dim): 1
Free-stream turb. kinetic energy (non-dim): 0.00375
Free-stream specific dissipation (non-dim): 0.000375

Initialize Jacobian structure (Navier-Stokes). MG level: 0.
Initialize Jacobian structure (SA model).

----------------- Integration and Numerics Preprocessing ----------------
Integration Preprocessing.
No centered scheme.
Numerics Preprocessing.

---------------------- Python Interface Preprocessing ---------------------
Setting customized boundary conditions for zone 0

------------------------------ Begin Solver -----------------------------


I noticed that the current release for macOS/Linux is v6.1.0 while for Windows it’s v6.0.0. Is the solution simply that I need to be using v6.1.0? If not, any help would be appreciated.

Thank you in advance for the feedback,

Nathan