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Restart flow-over-heated-plate/fluid-su2 using initial condition #675

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Merged
MakisH merged 7 commits into from
May 15, 2026
Merged

Restart flow-over-heated-plate/fluid-su2 using initial condition #675

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6802226
Add initial condition + restart from that for SU2-FOHP
j-signorelli Oct 11, 2025
2b91cd9
Merge branch 'develop' into add_su2_ic_fohp
MakisH Jan 12, 2026
235b7ea
Use an actually quiescent flowfield
j-signorelli Feb 16, 2026
8abf45e
Merge branch 'develop' into add_su2_ic_fohp
MakisH May 12, 2026
b8c86c5
Add changelog entry
MakisH May 12, 2026
d0ac763
Add initial state config and add a note
MakisH May 12, 2026
d052cf0
minor clarity tweaks
j-signorelli May 15, 2026
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1 change: 1 addition & 0 deletions changelog-entries/675.md
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- Changed the `flow-over-heated-plate/fluid-su2` case to use a restart file for the initial condition. [#675](https://github.com/precice/tutorials/pull/675)
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221 changes: 221 additions & 0 deletions flow-over-heated-plate/fluid-su2/laminar_config_ic.cfg
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Physical governing equations (EULER, NAVIER_STOKES,
% WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
% POISSON_EQUATION)
SOLVER= NAVIER_STOKES
%
% Specify turbulence model (NONE, SA, SA_NEG, SST)
KIND_TURB_MODEL= NONE
%
% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
MATH_PROBLEM= DIRECT
%
% Restart solution (NO, YES)
RESTART_SOL= NO

% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 2.88e-4
%
% Angle of attack (degrees, only for compressible flows)
AOA= 0.0
%
% Side-slip angle (degrees, only for compressible flows)
SIDESLIP_ANGLE= 0.0
%
% Free-stream temperature (288.15 K by default)
FREESTREAM_TEMPERATURE= 300
%
% Free-stream pressure (101325.0 N/m^2, 2116.216 psf by default)
FREESTREAM_PRESSURE= 103500
%
% Init option to choose between Reynolds (default) or thermodynamics quantities
% for initializing the solution (REYNOLDS, TD_CONDITIONS)
INIT_OPTION= TD_CONDITIONS
%
% Free-stream option to choose between density and temperature (default) for
% initializing the solution (TEMPERATURE_FS, DENSITY_FS)
FREESTREAM_OPTION= TEMPERATURE_FS
%
% Compressible flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
REF_DIMENSIONALIZATION= DIMENSIONAL
%
% ---- NONEQUILIBRIUM GAS, IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS, CoolProp library -------%
%
% Fluid model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS,
% CONSTANT_DENSITY, INC_IDEAL_GAS, INC_IDEAL_GAS_POLY, MUTATIONPP, SU2_NONEQ, FLUID_MIXTURE, COOLPROP)
FLUID_MODEL= IDEAL_GAS
% Ratio of specific heats (1.4 default and the value is hardcoded
% for the model STANDARD_AIR, compressible only)
GAMMA_VALUE= 1.0741
%
% Specific gas constant (287.058 J/kg*K default and this value is hardcoded
% for the model STANDARD_AIR, compressible only)
GAS_CONSTANT= 345
%
% --------------------------- VISCOSITY MODEL ---------------------------------%
%
% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY, POLYNOMIAL_VISCOSITY).
VISCOSITY_MODEL= CONSTANT_VISCOSITY
%
% Molecular Viscosity that would be constant (1.716E-5 by default)
MU_CONSTANT= 0.0002
% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
%
% Laminar Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL,
% POLYNOMIAL_CONDUCTIVITY).
CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
%
% Laminar Prandtl number (0.72 (air), only for CONSTANT_PRANDTL)
PRANDTL_LAM= 0.01
% ------------------------- TIME-DEPENDENT SIMULATION -------------------------------%
%
% Time domain simulation
TIME_DOMAIN= NO
ITER= 1

% Inner iter convergence
CONV_FIELD= RMS_DENSITY, RMS_ENERGY
CONV_RESIDUAL_MINVAL= -9
CONV_STARTITER= 0

% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
% This is used for the inner iterations of dual time-stepping
TIME_DISCRE_FLOW= EULER_IMPLICIT
%
% ----------------------- BODY FORCE DEFINITION -------------------------------%
%
% Apply a body force as a source term (NO, YES)
BODY_FORCE= YES
%
% Vector of body force values (BodyForce_X, BodyForce_Y, BodyForce_Z)
BODY_FORCE_VECTOR= ( 0.0, -9.81, 0.0 )
% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
MARKER_FAR= (inlet, outlet)
%
%MARKER_HEATFLUX= (bottom, 0, interface, 0)
%
MARKER_SYM= (slip_bottom, top, bottom, interface)
%
% Marker(s) of the surface where custom thermal BCs are defined.
%MARKER_PYTHON_CUSTOM = ( interface )
%
% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
%
% Courant-Friedrichs-Lewy condition of the finest grid
% Important for inner iterations
CFL_NUMBER= 1.0
%
% Adaptive CFL number (NO, YES)
CFL_ADAPT= YES
%
% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
% CFL max value )
CFL_ADAPT_PARAM= ( 0.1, 1.1, 0.1, 100.0 )
%
% Number of total iterations
TIME_ITER= 99999
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
%
% Linear solver for implicit formulations (BCGSTAB, FGMRES)
LINEAR_SOLVER= FGMRES
%
% Preconditioner of the Krylov linear solver (JACOBI, LINELET, LU_SGS)
LINEAR_SOLVER_PREC= ILU
%
% Minimum error of the linear solver for implicit formulations
LINEAR_SOLVER_ERROR= 1E-10
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 20

% -------------------------- MULTIGRID PARAMETERS -----------------------------%
%
% Multi-grid levels (0 = no multi-grid)
MGLEVEL= 3
%
% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
MGCYCLE= V_CYCLE
%
% Multi-grid pre-smoothing level
MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
%
% Multi-grid post-smoothing level
MG_POST_SMOOTH= ( 0, 0, 0, 0 )
%
% Jacobi implicit smoothing of the correction
MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
%
% Damping factor for the residual restriction
MG_DAMP_RESTRICTION= 0.75
%
% Damping factor for the correction prolongation
MG_DAMP_PROLONGATION= 0.75

% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
% TURKEL_PREC, MSW)
CONV_NUM_METHOD_FLOW= ROE
%
% Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations.
% Required for 2nd order upwind schemes (NO, YES)
MUSCL_FLOW= YES
%
% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG,
% BARTH_JESPERSEN, VAN_ALBADA_EDGE)
SLOPE_LIMITER_FLOW= NONE
%
% Coefficient for the limiter (smooth regions)
VENKAT_LIMITER_COEFF= 0.05
%
% 2nd and 4th order artificial dissipation coefficients
JST_SENSOR_COEFF= ( 0.5, 0.02 )
%
%
% ------------------------- SCREEN/HISTORY VOLUME OUTPUT --------------------------%
% Screen output fields (use 'SU2_CFD -d <config_file>' to view list of available fields)
SCREEN_OUTPUT= (TIME_ITER, CUR_TIME, INNER_ITER, REL_RMS_DENSITY, RMS_DENSITY, RMS_ENERGY)
%
% History output groups (use 'SU2_CFD -d <config_file>' to view list of available fields)
HISTORY_OUTPUT= (ITER, RMS_RES)
%
% Volume output fields/groups (use 'SU2_CFD -d <config_file>' to view list of available fields)
VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE)
%
%
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
% Mesh input file
MESH_FILENAME= fluid_mesh.su2
%
% Mesh input file format (SU2, CGNS, NETCDF_ASCII)
MESH_FORMAT= SU2
%
% Restart flow input file
% SOLUTION_FILENAME= restart_flow.dat
%
% Files to output
% Possible formats : (TECPLOT_ASCII, TECPLOT, SURFACE_TECPLOT_ASCII,
% SURFACE_TECPLOT, CSV, SURFACE_CSV, PARAVIEW_ASCII, PARAVIEW_LEGACY, SURFACE_PARAVIEW_ASCII,
% SURFACE_PARAVIEW_LEGACY, PARAVIEW, SURFACE_PARAVIEW, RESTART_ASCII, RESTART, CGNS, SURFACE_CGNS, STL_ASCII, STL_BINARY)
% default : (RESTART, PARAVIEW, SURFACE_PARAVIEW)
OUTPUT_FILES= (RESTART, PARAVIEW)
%
OUTPUT_WRT_FREQ= 10000, 10000
%
% Output file restart flow
RESTART_FILENAME= restart_flow.dat
%
% Output file convergence history (w/o extension)
CONV_FILENAME= history
%
% Output file flow (w/o extension) variables
VOLUME_FILENAME= flow

8 changes: 6 additions & 2 deletions flow-over-heated-plate/fluid-su2/laminar_config_unsteady.cfg
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Expand Up @@ -12,7 +12,8 @@ KIND_TURB_MODEL= NONE
MATH_PROBLEM= DIRECT
%
% Restart solution (NO, YES)
RESTART_SOL= NO
RESTART_SOL= YES
RESTART_ITER= 1

% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
Expand Down Expand Up @@ -212,7 +213,10 @@ MESH_FILENAME= fluid_mesh.su2
MESH_FORMAT= SU2
%
% Restart flow input file
% SOLUTION_FILENAME= restart_flow.dat
% Uniform freestream initial condition generated using laminar_config_ic.cfg
% and renaming the resulting restart_flow.dat file to initial_flow_00000.dat.
% See https://github.com/precice/tutorials/pull/675 for details.
SOLUTION_FILENAME= initial_flow.dat
%
% Files to output
% Possible formats : (TECPLOT_ASCII, TECPLOT, SURFACE_TECPLOT_ASCII,
Expand Down
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