Boundary Markers

Generated from SU2 commit 6b54b78464 on 2026-10-23. Do not edit this page. Edit the comment above the option in Common/src/CConfig.cpp instead.

MARKER_PLOTTING

Marker(s) of the surface in the surface flow solution file

• Type: list of strings
• In config_template.cfg: MARKER_PLOTTING = ( airfoil )
• Mentioned in: History and Solution Output, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Shape Optimization with the Discrete Adjoint, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Unsteady Flows and DES, Aachen turbine stage with Mixing-plane and 1 more
• Used in 312 test case files, for example: aeroelastic_NACA64A010.cfg (( airfoil )), backwardStep.cfg (( WALL_BOTTOM )), config.cfg (( InnerWall ))
• Code: CConfig.cpp line 1603

MARKER_MONITORING

Marker(s) of the surface where evaluate the non-dimensional coefficients

More in config_template.cfg: Marker(s) of the surface where the non-dimensional coefficients are evaluated.

• Type: list of strings
• In config_template.cfg: MARKER_MONITORING = ( airfoil )
• Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Shape Optimization with the Discrete Adjoint, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Unsteady Flows and DES and 4 more
• Used in 321 test case files, for example: aeroelastic_NACA64A010.cfg (( airfoil )), air_nozzle_restart.cfg ((WALL)), config.cfg (( InnerWall ))
• Code: CConfig.cpp line 1605

MARKER_CREATE_COPY

Marker(s) for which to create copies when reading the mesh

More in config_template.cfg: Duplicate markers while reading the mesh. Currently this is only used for thermoelastic simulations to allow specifying two boundary conditions (thermal and structural) on the same boundary.

• Type: list of strings
• In config_template.cfg: MARKER_CREATE_COPY= ( original_1, copy_1, ..., original_n, copy_n )
• Mentioned in: Changes in Version 8
• Used in 4 test case files, for example: configBeamNonlinear_3d.cfg (( left, left_heat, right, right_heat )), configFEA.cfg (( clamped, isothermal ))
• Code: CConfig.cpp line 1608

MARKER_ANALYZE

Marker(s) of the surface in the surface flow solution file

More in config_template.cfg: Marker(s) of the surface that is going to be analyzed in detail (massflow, average pressure, distortion, etc)

• Type: list of strings
• In config_template.cfg: MARKER_ANALYZE = ( airfoil )
• Mentioned in: Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Shape Optimization with the Discrete Adjoint, Setup Guide: Species Transport and Combustion, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane and 1 more
• Used in 62 test case files, for example: inv_wedge_ROE.cfg ((outlet)), fluid.cfg (( cylinder_fluid )), Arina2KRS.cfg (( WALL1 ))
• Code: CConfig.cpp line 1611

MARKER_DESIGNING

Marker(s) of the surface where objective function (design problem) will be evaluated

More in config_template.cfg: Marker(s) of the surface where obj. func. (design problem) will be evaluated

• Type: list of strings
• In config_template.cfg: MARKER_DESIGNING = ( airfoil )
• Used in 60 test case files, for example: inv_ONERAM6.cfg (( WING )), def_cylindrical.cfg (( CYLINDER )), def_NACA0012.cfg (( airfoil ))
• Code: CConfig.cpp line 1613

GEO_MARKER

Marker(s) of the surface where evaluate the geometrical functions

More in config_template.cfg: Marker(s) of the surface where geometrical based function will be evaluated

• Type: list of strings
• In config_template.cfg: GEO_MARKER= ( airfoil )
• Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, Constrained shape design of a transonic inviscid wing at a cte. C_L
• Used in 20 test case files, for example: turb_ONERAM6.cfg (( wing )), naca0012.cfg (( airfoil )), Arina2KRS.cfg (( WALL1 ))
• Code: CConfig.cpp line 1615

MARKER_EULER

Euler wall boundary marker(s)

More in config_template.cfg: Euler wall boundary marker(s) (NONE = no marker) Implementation identical to MARKER_SYM.

• Type: list of strings
• In config_template.cfg: MARKER_EULER= ( airfoil )
• Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Shape Optimization with the Discrete Adjoint, Inviscid Bump in a Channel, Inviscid Hydrofoil and 1 more
• Used in 135 test case files, for example: aeroelastic_NACA64A010.cfg (( airfoil )), inv_ONERAM6.cfg (( WING )), inv_wedge_ROE.cfg (( upper, lower ))
• Code: CConfig.cpp line 1617

MARKER_FAR

Far-field boundary marker(s)

More in config_template.cfg: Far-field boundary marker(s) (NONE = no marker)

• Type: list of strings
• In config_template.cfg: MARKER_FAR= ( farfield )
• Mentioned in: Markers and Boundary Conditions, Physical Definition, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Non-Ideal Compressible Flows and 5 more
• Used in 189 test case files, for example: aeroelastic_NACA64A010.cfg (( farfield )), config.cfg (( Inlet, Outlet )), inv_ONERAM6.cfg (( FARFIELD ))
• Code: CConfig.cpp line 1619

MARKER_SYM

Symmetry boundary condition

More in config_template.cfg: Symmetry boundary marker(s) (NONE = no marker) Implementation identical to MARKER_EULER.

• Type: list of strings
• In config_template.cfg: MARKER_SYM= ( NONE )
• Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Shape Optimization with the Discrete Adjoint, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics and 3 more
• Used in 118 test case files, for example: air_nozzle_restart.cfg (( SYMMETRY )), backwardStep.cfg (( SYMMETRY_TOP, SYMMETRY_BOTTOM )), turb_ONERAM6.cfg (( symmetry ))
• Code: CConfig.cpp line 1621

MARKER_NEARFIELD

Near-Field boundary condition

More in config_template.cfg: Near-Field boundary marker(s) (NONE = no marker)

• Type: list of strings
• In config_template.cfg: MARKER_NEARFIELD= ( NONE )
• Used in 3 test case files, for example: Arina2KRS.cfg (( NONE )), BIPARABOLIC.cfg (( upper_nearfield, lower_nearfield )), NACA64206.cfg (( Nearfield ))
• Code: CConfig.cpp line 1623

MARKER_FLUID_INTERFACE

Fluid interface boundary marker(s)

• Type: list of strings
• In config_template.cfg: MARKER_FLUID_INTERFACE= ( NONE )
• Mentioned in: Setup Guide: Turbomachinery
• Used in 25 test case files, for example: Arina2KRS.cfg (( NONE )), circles.cfg ((OUTMIX, INMIX)), bars.cfg ((outflow_bars, inflow_channel))
• Code: CConfig.cpp line 1625

MARKER_DEFORM_MESH

Deformable marker(s) at the interface

More in config_template.cfg: Moving markers which deform the mesh

• Type: list of strings
• In config_template.cfg: MARKER_DEFORM_MESH = ( airfoil )
• Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, Dynamic Fluid-Structure Interaction (FSI) using the Python wrapper and a Nastran structural model, Static Fluid-Structure Interaction (FSI)
• Used in 13 test case files, for example: configFlow.cfg (( leading_edge, pressure_side, suction_side )), configFlow.cfg (( UpperWall, LowerWall )), configFlow.cfg ((wallUpwF, wallDownF, wallUpperF))
• Code: CConfig.cpp line 1627

MARKER_DEFORM_MESH_SYM_PLANE

Symmetry plane for mesh deformation only

• Type: list of strings
• In config_template.cfg: MARKER_DEFORM_MESH_SYM_PLANE = ( wall )
• Mentioned in: Dynamic Fluid-Structure Interaction (FSI) using the Python wrapper and a Nastran structural model
• Used in 2 test case files, for example: configFlow.cfg (( upper ))
• Code: CConfig.cpp line 1629

MARKER_DEFORM_MESH_INTERNAL

Internal marker for mesh deformation only

• Type: list of strings
• Not in config_template.cfg.
• Code: CConfig.cpp line 1631

MARKER_FLUID_LOAD

Marker(s) in which the flow load is computed/applied

• Type: list of strings
• In config_template.cfg: MARKER_FLUID_LOAD= ( NONE )
• Mentioned in: Static Fluid-Structure Interaction (FSI)
• Used in 10 test case files, for example: configFEA.cfg (( pressure_side_s, suction_side_s )), configFEA.cfg (( LowerWallS, UpperWallS)), configFEA.cfg (( pressure_side_s, suction_side_s, clamped ))
• Code: CConfig.cpp line 1633

MARKER_ZONE_INTERFACE

ZONE interface boundary marker(s)

• Type: list of strings
• In config_template.cfg: MARKER_ZONE_INTERFACE= ( NONE )
• Mentioned in: Basics of Multi-Zone Computations, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane, Solid-to-Solid Conjugate Heat Transfer with Contact Resistance, Static Conjugate Heat Transfer (CHT) and 1 more
• Used in 50 test case files, for example: cht_2d_3cylinders.cfg ((cylinder_outer1, cylinder_inner1, cylinder_outer2, cylinder_inner2, cylinder_outer3, cylinder_inner3)), chtMaster.cfg (( cylinder_fluid, cylinder_solid )), circles.cfg ((OUTMIX, INMIX))
• Code: CConfig.cpp line 1635

MARKER_CHT_INTERFACE

CHT interface boundary marker(s)

• Type: list of strings
• In config_template.cfg: MARKER_CHT_INTERFACE= ( NONE )
• Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer, Solid-to-Solid Conjugate Heat Transfer with Contact Resistance, Static Conjugate Heat Transfer (CHT)
• Used in 15 test case files, for example: cht_2d_3cylinders.cfg ((cylinder_outer1, cylinder_inner1, cylinder_outer2, cylinder_inner2, cylinder_outer3, cylinder_inner3)), chtMaster.cfg (( cylinder_fluid, cylinder_solid )), configFEA.cfg (( wallS ))
• Code: CConfig.cpp line 1637

CHT_INTERFACE_CONTACT_RESISTANCE

: Thermal contact resistance values for each CHT inerface.

• Type: list of real numbers
• Not in config_template.cfg.
• Mentioned in: Changes in Version 8, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Solid-to-Solid Conjugate Heat Transfer with Contact Resistance
• Code: CConfig.cpp line 1639

MARKER_INTERNAL

Internal boundary marker(s)

More in config_template.cfg: Internal boundary marker(s) e.g. no boundary condition (NONE = no marker)

• Type: list of strings
• In config_template.cfg: MARKER_INTERNAL= ( NONE )
• Used in 4 test case files, for example: Arina2KRS.cfg (( NONE )), naca0012.cfg (( FWH1 ))
• Code: CConfig.cpp line 1641

MARKER_CUSTOM

Custom boundary marker(s)

More in config_template.cfg: Custom boundary marker(s) (this has to be implemented by users in the code).

• Type: list of strings
• In config_template.cfg: MARKER_CUSTOM= ( NONE )
• Used in 18 test case files, for example: Ringleb.cfg (( BottomBoundary, LeftBoundary, RightBoundary, TopBoundary )), Ringleb_WallBC.cfg (( BottomBoundary, TopBoundary )), lam_mms_dg_3d.cfg (( PlaneZ0 ))
• Code: CConfig.cpp line 1643

MARKER_PERIODIC

Periodic boundary marker(s) Format: ( periodic marker, donor marker, rotation_center_x, rotation_center_y, rotation_center_z, rotation_angle_x-axis, rotation_angle_y-axis, rotation_angle_z-axis, translation_x, translation_y, translation_z, … )

More in config_template.cfg: Periodic boundary marker(s) (NONE = no marker) Format: ( periodic marker, donor marker, rotation_center_x, rotation_center_y, rotation_center_z, rotation_angle_x-axis, rotation_angle_y-axis, rotation_angle_z-axis, translation_x, translation_y, translation_z, … )

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_PERIODIC= ( NONE )
• Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane, Streamwise Periodic Flow
• Used in 32 test case files, for example: backwardStep.cfg (( Y-2, Y2, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.05, 0.0)), circles.cfg (( PER1, PER2, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 20.0, 0.0, PER3, PER4, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 20.0, 0.0)), Axial_stage2D.cfg (( periodic1, periodic2, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.04463756775, 0.0, periodic3, periodic4, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.04463756775, 0.0))
• Code: CConfig.cpp line 1648

MARKER_PYTHON_CUSTOM

Python customizable marker(s)

More in config_template.cfg: Marker(s) of the surface where custom thermal BC’s are defined.

• Type: list of strings
• In config_template.cfg: MARKER_PYTHON_CUSTOM = ( NONE )
• Mentioned in: Flamelet Solver — Python Wrapper Wall Boundary Conditions, User Defined combustion model with Python
• Used in 2 test case files, for example: Arina2KRS.cfg (( NONE )), unsteady_CHT_FlatPlate_Conf.cfg ((plate))
• Code: CConfig.cpp line 1652

PYTHON_CUSTOM_SOURCE

Python custom source

• Type: YES / NO
• Default: NO
• Not in config_template.cfg.
• Mentioned in: Changes in Version 8, User Defined combustion model with Python, Wind velocity and pollutant dispersion in a city
• Used in 2 test case files, for example: lam_buoyancy_cavity.cfg (YES)
• Code: CConfig.cpp line 1655

MARKER_WALL_FUNCTIONS

Viscous wall markers for which wall functions must be applied. Format: (Wall function marker, wall function type, …)

More in config_template.cfg: Viscous wall markers for which wall functions must be applied. (NONE = no marker) Format: ( marker name, wall function type -NO_WALL_FUNCTION, STANDARD_WALL_FUNCTION, ADAPTIVE_WALL_FUNCTION, SCALABLE_WALL_FUNCTION, EQUILIBRIUM_WALL_MODEL, NONEQUILIBRIUM_WALL_MODEL-, … )

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_WALL_FUNCTIONS= ( airfoil, NO_WALL_FUNCTION )
• Mentioned in: Markers and Boundary Conditions, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Turbomachinery, Wall Treatment: Wall Functions and Roughness, Aachen turbine stage with Mixing-plane, Turbulent Bend with wall functions
• Used in 6 test case files, for example: aachen_3D_MP_restart.cfg (( BLADE1, STANDARD_WALL_FUNCTION , BLADE2, STANDARD_WALL_FUNCTION , BLADE3, STANDARD_WALL_FUNCTION , HUB1, STANDARD_WALL_FUNCTION , SHROUD1, STANDARD_WALL_FUNCTION , HUB2, STANDARD_WALL_FUNCTION , SHROUD2, STANDARD_WALL_FUNCTION , HUB3, STANDARD_WALL_FUNCTION , SHROUD3, STANDARD_WALL_FUNCTION )), turb_SA_flatplate.cfg (( wall, STANDARD_WALL_FUNCTION ))
• Code: CConfig.cpp line 1659

MARKER_SPECIES_STRONG_BC

Markers where a strong BC must be applied.

• Type: list of strings
• Not in config_template.cfg.
• Mentioned in: Changes in Version 8, Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Incompressible, Laminar Combustion Simulation, Species Transport
• Used in 12 test case files, for example: lam_prem_ch4_cfd.cfg ((inlet, outlet, wall)), lam_prem_ch4_hx_ad.cfg ((inlet, wall_burner, wall_hx)), lam_prem_ch4_cht_cfd_fluid.cfg ((inlet, outlet, wall_burner))
• Code: CConfig.cpp line 1663

ACTDISK_TYPE

Actuator Disk boundary type

More in config_template.cfg: Actuator disk boundary type (VARIABLE_LOAD, VARIABLES_JUMP, BC_THRUST, DRAG_MINUS_THRUST, BLADE_ELEMENT)

• Type: one of the values below
• Values: VARIABLES_JUMP, BC_THRUST, NET_THRUST, DRAG_MINUS_THRUST, MASSFLOW, POWER, VARIABLE_LOAD, BLADE_ELEMENT
• Default: VARIABLES_JUMP
• In config_template.cfg: ACTDISK_TYPE= VARIABLES_JUMP
• Mentioned in: Changes in Version 8, Actuator Disk With Variable Load
• Used in 3 test case files, for example: actuatordisk_bem.cfg (BLADE_ELEMENT), propeller_variable_load.cfg (VARIABLE_LOAD), propeller.cfg (VARIABLES_JUMP)
• Code: CConfig.cpp line 1666

MARKER_ACTDISK

Actuator disk boundary marker(s) with the following formats (NONE = no marker) Variable Load: (inlet face marker, outlet face marker, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0) Variables Jump: ( inlet face marker, outlet face marker, Takeoff pressure jump (psf), Takeoff temperature jump (R), Takeoff rev/min, Cruise pressure jump (psf), Cruise temperature jump (R), Cruise rev/min ) BC Thrust: ( inlet face marker, outlet face marker, Takeoff BC thrust (lbs), 0.0, Takeoff rev/min, Cruise BC thrust (lbs), 0.0, Cruise rev/min ) Drag-Thrust: ( inlet face marker, outlet face marker, Takeoff Drag-Thrust (lbs), 0.0, Takeoff rev/min, Cruise Drag-Thrust (lbs), 0.0, Cruise rev/min ) Blade element: ( inlet face marker, outlet face marker, Takeoff Drag-Thrust (lbs), 0.0, Takeoff rev/min, Cruise Drag-Thrust (lbs), 0.0, Cruise rev/min ) (from config_template.cfg)

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_ACTDISK= ( NONE )
• Mentioned in: Actuator Disk With Variable Load
• Used in 3 test case files, for example: actuatordisk_bem.cfg (( ACTDISK_IN, ACTDISK_OUT , 0.0, 0.0, 12715.2, 0.0, 0.0, 12715.2)), propeller_variable_load.cfg (( DISK, DISK_BACK, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0 )), propeller.cfg (( ACTDISK, ACTDISK_BACK, 70.5, 10, 0, 70.5, 10, 0 ))
• Code: CConfig.cpp line 1669

MARKER_ACTDISK_BEM_CG

Actuator disk CG for blade element momentum (BEM) method.

More in config_template.cfg: Blade element: ( inlet face marker, outlet face marker, X_CG of inlet, Y_CG of inlet, Z_CG of inlet, X_CG of outlet, Y_CG of outlet, Z_CG of outlet )

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_ACTDISK_BEM_CG= ( NONE )
• Used in 1 test case file, for example: actuatordisk_bem.cfg (( ACTDISK_IN, ACTDISK_OUT, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0 ))
• Code: CConfig.cpp line 1674

MARKER_ACTDISK_BEM_AXIS

Actuator disk axis for blade element momentum (BEM) method.

More in config_template.cfg: Blade element: ( inlet face marker, outlet face marker, X_Axis of inlet, Y_Axis of inlet, Z_Axis of inlet, X_Axis of outlet, Y_Axis of outlet, Z_Axis of outlet )

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_ACTDISK_BEM_AXIS= ( NONE )
• Used in 1 test case file, for example: actuatordisk_bem.cfg (( ACTDISK_IN, ACTDISK_OUT, 1.0, 0.0, 0.0, 1.0, 0.0, 0.0 ))
• Code: CConfig.cpp line 1679

ACTDISK_FILENAME

Input file for a specified actuator disk (w/ extension)

More in config_template.cfg: Actuator disk data input file name

• Type: string
• Default: string("actdiskinput.dat")
• In config_template.cfg: ACTDISK_FILENAME= actuatordisk.dat
• Mentioned in: Actuator Disk With Variable Load
• Used in 1 test case file, for example: propeller_variable_load.cfg (ActuatorDisk.dat)
• Code: CConfig.cpp line 1684

INLET_TYPE

Inlet boundary type

More in config_template.cfg: Inlet boundary type (TOTAL_CONDITIONS, MASS_FLOW)

• Type: one of the values below
• Values: TOTAL_CONDITIONS, MASS_FLOW, INPUT_FILE, VELOCITY_INLET, PRESSURE_INLET
• Default: TOTAL_CONDITIONS
• In config_template.cfg: INLET_TYPE= TOTAL_CONDITIONS
• Mentioned in: Markers and Boundary Conditions, Inviscid Bump in a Channel
• Used in 12 test case files, for example: Arina2KRS.cfg (TOTAL_CONDITIONS), inv_cylinder3D.cfg (MASS_FLOW)
• Code: CConfig.cpp line 1687

INLET_USE_NORMAL

Use the local boundary normal for the flow direction with pressure inlets.

More in config_template.cfg: Impose inlet velocity magnitude in the direction of the normal of the inlet face. used for incompressible velocity inlet and for compressible pressure and mass flow inlets.

• Type: YES / NO
• Default: NO
• In config_template.cfg: INLET_USE_NORMAL= NO
• Mentioned in: Changes in Version 8
• Code: CConfig.cpp line 1689

INC_INLET_TYPE

List of inlet types for incompressible flows. List length must match number of inlet markers. Options: VELOCITY_INLET, PRESSURE_INLET, INPUT_FILE.

• Type: list of the values below
• Values: TOTAL_CONDITIONS, MASS_FLOW, INPUT_FILE, VELOCITY_INLET, PRESSURE_INLET
• In config_template.cfg: INC_INLET_TYPE= VELOCITY_INLET
• Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Inviscid Hydrofoil, Turbulent Bend with wall functions
• Used in 53 test case files, for example: backwardStep.cfg (VELOCITY_INLET), lam_partial_prem_ch4_cfd.cfg (VELOCITY_INLET,VELOCITY_INLET), inv_nozzle.cfg (PRESSURE_INLET)
• Code: CConfig.cpp line 1691

SPECIFIED_INLET_PROFILE

Read inlet profile from a file (YES, NO) default: NO (from config_template.cfg)

• Type: YES / NO
• Default: NO
• In config_template.cfg: SPECIFIED_INLET_PROFILE= NO
• Mentioned in: Setup Guide: Incompressible Flows, Composition-Dependent model for Species Transport equations, Laminar Backward-facing Step, Turbulent Bend with wall functions
• Used in 25 test case files, for example: def_intersect.cfg (NO), config.cfg (YES)
• Code: CConfig.cpp line 1692

INLET_FILENAME

Input file for a specified inlet profile (w/ extension)

More in config_template.cfg: File specifying inlet profile

• Type: string
• Default: string("inlet.dat")
• In config_template.cfg: INLET_FILENAME= inlet.dat
• Mentioned in: Setup Guide: Incompressible Flows, Laminar Backward-facing Step, Turbulent Bend with wall functions
• Used in 23 test case files, for example: def_intersect.cfg (inletVelocity.dat), config.cfg (inlet.dat), profile_poiseuille.cfg (inlet_poiseuille.dat)
• Code: CConfig.cpp line 1694

INLET_MATCHING_TOLERANCE

If a file is provided to specify the inlet profile, this tolerance will be used to match the coordinates in the input file to the points on the grid.

• Type: real number
• Default: 1e-6
• In config_template.cfg: % INLET_MATCHING_TOLERANCE= 1e-6
• Used in 4 test case files, for example: def_intersect.cfg (1e-5), psi.cfg (1e-4)
• Code: CConfig.cpp line 1699

MARKER_INLET

Inlet boundary marker(s) with the following formats, Total Conditions: (inlet marker, total temp, total pressure, flow_direction_x, flow_direction_y, flow_direction_z, … ) where flow_direction is a unit vector. Mass Flow: (inlet marker, density, velocity magnitude, flow_direction_x, flow_direction_y, flow_direction_z, … ) where flow_direction is a unit vector.

More in config_template.cfg: Inlet boundary marker(s) with the following formats (NONE = no marker) Total Conditions: (inlet marker, total temp, total pressure, flow_direction_x, flow_direction_y, flow_direction_z, … ) where flow_direction is a unit vector. Mass Flow: (inlet marker, density, velocity magnitude, flow_direction_x, flow_direction_y, flow_direction_z, … ) where flow_direction is a unit vector. Inc. Velocity: (inlet marker, temperature, velocity magnitude, flow_direction_x, flow_direction_y, flow_direction_z, … ) where flow_direction is a unit vector. Inc. Pressure: (inlet marker, temperature, total pressure, flow_direction_x, flow_direction_y, flow_direction_z, … ) where flow_direction is a unit vector.

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_INLET= ( NONE )
• Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Turbomachinery, Setup Guide: Unsteady Flows and DES and 9 more
• Used in 93 test case files, for example: backwardStep.cfg (( INLET, 298.333, 44.316, 1.0, 0.0, 0.0 )), ddes_flatplate.cfg (( inlet, 302.4, 118309.784, 1.0, 0.0, 0.0 )), def_intersect.cfg ((inlet, 300.0, 1.0, 1.0, 0.0, 0.0))
• Code: CConfig.cpp line 1707

MARKER_INLET_SPECIES

Inlet Species boundary marker(s) with the following format Inlet Species: (inlet_marker, Species1, Species2, …, SpeciesN-1, inlet_marker2, Species1, Species2, …)

More in config_template.cfg: Inlet Species boundary marker(s) with the following format: (inlet_marker, Species1, Species2, …, SpeciesN-1, inlet_marker2, Species1, Species2, …) For N species, N-1 transport equations are solved, the last one Y_N is solved algebraically as 1-(sum of the species 1 to (N-1))

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_INLET_SPECIES= (inlet, 0.5, ..., inlet2, 0.6, ...)
• Mentioned in: Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Incompressible, Laminar Combustion Simulation, Incompressible, Laminar counterflow diffusion flame, Species Transport
• Used in 31 test case files, for example: air_nozzle_species.cfg (( INFLOW, 0.5 )), lam_prem_ch4_cfd.cfg ((inlet, 0, -193600.0, 0.0, 0.0)), lam_prem_ch4_hx_ad.cfg ((inlet, 0.0, 0.0, 0.0, 0.0))
• Code: CConfig.cpp line 1710

MARKER_INLET_TURBULENT

Inlet Turbulence boundary marker(s) with the following format Inlet Turbulent: (inlet_marker, TurbulentIntensity1, ViscosityRatio1, inlet_marker2, TurbulentIntensity2, ViscosityRatio2, …)

More in config_template.cfg: Inlet Turbulent boundary marker(s) with the following format: SA Model: (inlet_marker1, NuFactor1, inlet_marker2, NuFactor2, …) SST Model: (inlet_marker1, TurbIntensity1, RatioTurbLamViscosity1, inlet_marker2, TurbIntensity2, RatioTurbLamViscosity2, …)

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_INLET_TURBULENT= (inlet1, 0.05, 15, inlet2, 0.02, ...)
• Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows, Transition Models, Turbulence Models, Composition-Dependent model for Species Transport equations, Turbulent Bend with wall functions
• Used in 4 test case files, for example: psi.cfg ((inlet, 0.10, 15)), species2_primitiveVenturi_mixingmodel_TURBULENT_MARKERS.cfg ((gas_inlet, 0.05, 15\), species2_primitiveVenturi_mixingmodel_viscosity.cfg ((gas_inlet, 5.0, \)
• Code: CConfig.cpp line 1714

MARKER_RIEMANN

Riemann boundary marker(s) with the following formats, a unit vector.

More in config_template.cfg: Riemann boundary marker(s) (NONE = no marker) Format: (marker, data kind flag, list of data)

• Type: special format, see config_template.cfg
• Values: See Riemann_Map. The variables indicated by the option and the flow direction unit vector must be specified.
• In config_template.cfg: MARKER_RIEMANN= ( NONE )
• Mentioned in: Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Turbomachinery, Non-ideal compressible flow in a supersonic nozzle
• Used in 27 test case files, for example: air_nozzle_restart.cfg (( INFLOW, TOTAL_CONDITIONS_PT, 1400000.0, 373.15, 1.0, 0.0, 0.0, \), turb_SA_PR.cfg ((inflow, TOTAL_CONDITIONS_PT, 13.8686E+05, 592.295, 1.0, 0.0, 0.0, outflow, STATIC_PRESSURE, 11.00E+05, 0.0, 0.0, 0.0, 0.0)), fluidModel.cfg (( INFLOW, TOTAL_CONDITIONS_PT, 904388, 542.13, 1.0, 0.0, 0.0, OUTFLOW, STATIC_PRESSURE, 200000.0, 0.0, 0.0, 0.0, 0.0 ))
• Code: CConfig.cpp line 1717

MARKER_WALL_SPECIES

Wall species boundary marker(s) with the following format: (marker_name, BC_TYPE, value, BC_TYPE, value, …) where BC_TYPE is either FLUX (Neumann) or VALUE (Dirichlet). Each marker must specify the same number of species (N species per marker).

More in config_template.cfg: Wall species boundary condition marker(s) for species transport (NONE = no marker) Specify either a Neumann flux boundary condition (FLUX) or a Dirichlet value boundary condition (VALUE) for each species independently. All markers must specify the same number of species. Format: ( marker_name, BC_TYPE_1, value_1, BC_TYPE_2, value_2, …, BC_TYPE_N, value_N, … ) where BC_TYPE is either FLUX (Neumann) or VALUE (Dirichlet) for each species Example for 3 species: MARKER_WALL_SPECIES= (wall1, FLUX, 0.0, VALUE, 0.3, VALUE, 0.2, wall2, VALUE, 0.1, VALUE, 0.4, FLUX, 0.0) If MARKER_WALL_SPECIES is not specified, a zero-flux boundary condition will be used.

• Type: special format, see config_template.cfg
• Values: See Wall_Map.
• In config_template.cfg: MARKER_WALL_SPECIES= ( NONE )
• Mentioned in: Changes in Version 8, Flamelet Solver — Python Wrapper Wall Boundary Conditions, Setup Guide: Species Transport and Combustion, Incompressible, Laminar counterflow diffusion flame
• Used in 1 test case file, for example: species3_primitiveVenturi_flux_value.cfg (( wall, VALUE, 1.0, FLUX, 0.01 ))
• Code: CConfig.cpp line 1722

MARKER_GILES

Giles boundary marker(s) with the following formats, a unit vector.

More in config_template.cfg: Giles boundary condition for inflow, outflow and mixing-plane Format inlet: ( marker, TOTAL_CONDITIONS_PT, Total Pressure , Total Temperature, Flow dir-norm, Flow dir-tang, Flow dir-span, under-relax-avg, under-relax-fourier) Format outlet: ( marker, STATIC_PRESSURE, Static Pressure value, -, -, -, -, under-relax-avg, under-relax-fourier) Format mixing-plane in and out: ( marker, MIXING_IN or MIXING_OUT, -, -, -, -, -, -, under-relax-avg, under-relax-fourier)

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_GILES= ( NONE )
• Mentioned in: Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 9 test case files, for example: Arina2KRS.cfg (( NONE )), circles.cfg ((INFLOW, TOTAL_CONDITIONS_PT, 1E6, 300, 1.0, 0.0, 0.0,1.0,1.0, OUTMIX, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0,1.0,1.0, INMIX, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0,1.0, 1.0, OUTFLOW, STATIC_PRESSURE, 9E5, 0.0, 0.0, 0.0, 0.0,1.0,1.0)), Axial_stage2D.cfg ((inflow, TOTAL_CONDITIONS_PT, 169623.33, 305.76, 1.0, 0.0, 0.0,1.0,1.0, outmix, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0,1.0,1.0, inmix, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0,1.0, 1.0 outflow, STATIC_PRESSURE, 99741.00, 0.0, 0.0, 0.0, 0.0,1.0,1.0))
• Code: CConfig.cpp line 1725

SPATIAL_FOURIER

Option to compute the spatial fourier trasformation for the Giles BC.

More in config_template.cfg: YES Non reflectivity activated, NO the Giles BC behaves as a normal 1D characteristic-based BC

• Type: YES / NO
• Default: NO
• In config_template.cfg: SPATIAL_FOURIER= NO
• Mentioned in: Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 8 test case files, for example: circles.cfg (YES), Jones_restart.cfg (NO)
• Code: CConfig.cpp line 1727

GILES_EXTRA_RELAXFACTOR

the 1st coeff the value of the under relaxation factor to apply to the shroud and hub, the 2nd coefficient is the the percentage of span-wise height influenced by this extra under relaxation factor.

More in config_template.cfg: This option insert an extra under relaxation factor for the Giles BC at the hub and shroud (under relax factor applied, span percentage to under relax)

• Type: fixed-size list of real numbers
• Default: Not extracted; see the code.
• In config_template.cfg: GILES_EXTRA_RELAXFACTOR= ( 0.05, 0.05)
• Mentioned in: Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 3 test case files, for example: Jones_restart.cfg ((0.05, 0.05))
• Code: CConfig.cpp line 1731

MIXINGPLANE_INTERFACE_KIND

types of mixing process for averaging quantities at the boundaries.

More in config_template.cfg: Specify kind of interpolation for the mixing-plane (LINEAR_INTERPOLATION, NEAREST_SPAN, MATCHING)

• Type: one of the values below
• Values: MATCHING, NEAREST_SPAN, LINEAR_INTERPOLATION
• Default: NEAREST_SPAN
• In config_template.cfg: MIXINGPLANE_INTERFACE_KIND= LINEAR_INTERPOLATION
• Mentioned in: Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 3 test case files, for example: Jones_restart.cfg (LINEAR_INTERPOLATION)
• Code: CConfig.cpp line 1734

AVERAGE_PROCESS_KIND

types of mixing process for averaging quantities at the boundaries.

More in config_template.cfg: Specify Kind of average process for linearizing the Navier-Stokes equation at inflow and outflow BCs included at the mixing-plane interface (ALGEBRAIC, AREA, MASSSFLUX, MIXEDOUT) default AREA

• Type: one of the values below
• Values: ALGEBRAIC, AREA, MIXEDOUT, MASSFLUX
• Default: AREA
• In config_template.cfg: AVERAGE_PROCESS_KIND= MIXEDOUT
• Mentioned in: Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 8 test case files, for example: circles.cfg (MIXEDOUT)
• Code: CConfig.cpp line 1737

PERFORMANCE_AVERAGE_PROCESS_KIND

types of mixing process for averaging quantities at the boundaries for performance computation.

More in config_template.cfg: Specify Kind of average process for computing turbomachinery performance parameters (ALGEBRAIC, AREA, MASSSFLUX, MIXEDOUT) default AREA

• Type: one of the values below
• Values: ALGEBRAIC, AREA, MIXEDOUT, MASSFLUX
• Default: AREA
• In config_template.cfg: PERFORMANCE_AVERAGE_PROCESS_KIND= MIXEDOUT
• Mentioned in: Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 8 test case files, for example: circles.cfg (MIXEDOUT)
• Code: CConfig.cpp line 1740

MIXEDOUT_COEFF

the 1st coeff is an under relaxation factor for the Newton method, the 2nd coefficient is the tolerance for the Newton method, 3rd coefficient is the maximum number of iteration for the Newton Method.

More in config_template.cfg: Parameters of the Newton method for the MIXEDOUT average algorithm (under relaxation factor, tollerance, max number of iterations)

• Type: fixed-size list of real numbers
• Default: Not extracted; see the code.
• In config_template.cfg: MIXEDOUT_COEFF= (1.0, 1.0E-05, 15)
• Mentioned in: Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 8 test case files, for example: circles.cfg ((1.0, 1.0E-05, 15)), multi_interface_rst.cfg ((1.0, 1.0E-05, 100))
• Code: CConfig.cpp line 1745

RAMP_MOTION_FRAME

option to ramp up or down the frame of motion velocity value

More in config_template.cfg: Specify ramp option for frame of motion (YES, NO) default NO

• Type: YES / NO
• Default: NO
• In config_template.cfg: RAMP_MOTION_FRAME= YES
• Mentioned in: Changes in Version 8, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 3 test case files, for example: rotor.cfg (YES), rotor_restart.cfg (NO)
• Code: CConfig.cpp line 1747

RAMP_MOTION_FRAME_COEFF

the 1st coeff is the staring outlet value, the 2nd coeff is the number of iterations for the update, 3rd is the number of total iteration till reaching the final outlet pressure value

More in config_template.cfg: Parameters of the frame of motion ramp (starting frame of motion speed, updating-iteration-frequency, total number of iteration for the ramp)

• Type: fixed-size list of real numbers
• Default: Not extracted; see the code.
• In config_template.cfg: RAMP_MOTION_FRAME_COEFF= (0.0, 39.0, 500)
• Mentioned in: Changes in Version 8, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 3 test case files, for example: rotor.cfg ((0.0, 39.0, 500))
• Code: CConfig.cpp line 1751

AVERAGE_MACH_LIMIT

AVERAGE_MACH_LIMIT is a limit value for average procedure based on the mass flux.

More in config_template.cfg: Limit of Mach number below which the mixedout algorithm is substituted with a AREA average algorithm to avoid numerical issues

• Type: real number
• Default: 0.03
• In config_template.cfg: AVERAGE_MACH_LIMIT= 0.05
• Mentioned in: Setup Guide: Turbomachinery
• Used in 8 test case files, for example: circles.cfg (0.05), transonic_stator.cfg (0.03)
• Code: CConfig.cpp line 1753

RAMP_OUTLET

option to ramp up or down the Giles outlet value

More in config_template.cfg: Specify ramp option for Outlet Giles value (YES, NO) default NO

• Type: YES / NO
• Default: NO
• In config_template.cfg: RAMP_OUTLET= NO
• Mentioned in: Changes in Version 8, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 7 test case files, for example: Axial_stage2D.cfg (NO)
• Code: CConfig.cpp line 1755

RAMP_OUTLET_COEFF

the 1st coeff is the staring outlet value, the 2nd coeff is the number of iterations for the update, 3rd is the number of total iteration till reaching the final outlet pressure value

More in config_template.cfg: Parameters of the outlet Giles ramp (starting outlet value, updating-iteration-frequency, total number of iteration for the ramp)

• Type: fixed-size list of real numbers
• Default: Not extracted; see the code.
• In config_template.cfg: RAMP_OUTLET_COEFF= (400000.0, 10.0, 500)
• Mentioned in: Changes in Version 8, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 6 test case files, for example: Axial_stage2D.cfg ((140000.0, 10.0, 2000)), transonic_stator.cfg ((700000.0, 10.0, 500)), Jones_restart.cfg ((400000.0, 10.0, 500))
• Code: CConfig.cpp line 1759

MARKER_MIXINGPLANE_INTERFACE

Identify the boundaries in which the mixing plane is applied.

More in config_template.cfg: Mixing-plane interface markers must be specified to activate the transfer of information between zones

• Type: list of strings
• In config_template.cfg: MARKER_MIXINGPLANE_INTERFACE= ( NONE )
• Mentioned in: Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 7 test case files, for example: Arina2KRS.cfg (( NONE )), circles.cfg ((OUTMIX, INMIX)), Axial_stage2D.cfg ((outmix, inmix))
• Code: CConfig.cpp line 1761

TURBULENT_MIXINGPLANE

Activate mixing plane also for turbulent quantities

More in config_template.cfg: Specify option for turbulent mixing-plane (YES, NO) default NO

• Type: YES / NO
• Default: NO
• In config_template.cfg: TURBULENT_MIXINGPLANE= YES
• Mentioned in: Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 6 test case files, for example: circles.cfg (YES)
• Code: CConfig.cpp line 1763

RELATIVE_FRAME_SLIDINGPLANE

Activate sliding plane for relative frame

• Type: YES / NO
• Default: NO
• Not in config_template.cfg.
• Code: CConfig.cpp line 1765

MARKER_TURBOMACHINERY

Identify the boundaries for which the turbomachinery settings are applied.

More in config_template.cfg: Inflow and Outflow markers must be specified, for each blade (zone), following the natural groth of the machine (i.e, from the first blade to the last)

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_TURBOMACHINERY= ( NONE )
• Mentioned in: Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 9 test case files, for example: Arina2KRS.cfg (( NONE )), circles.cfg ((INFLOW, OUTMIX, INMIX, OUTFLOW)), Axial_stage2D.cfg ((inflow, outmix, inmix, outflow))
• Code: CConfig.cpp line 1767

NUM_SPANWISE_SECTIONS

Integer number of spanwise sections to compute 3D turbo BC and Performance for turbomachinery

• Type: integer
• Default: 1
• In config_template.cfg: NUM_SPANWISE_SECTIONS= 1
• Mentioned in: Setup Guide: Turbomachinery
• Code: CConfig.cpp line 1769

SPANWISE_KIND

type of algorithm to identify the span-wise sections at the turbo boundaries.

More in config_template.cfg: type of algorithm to identify the span-wise sections at the turbo boundaries. 1 means automatic.

• Type: one of the values below
• Values: AUTOMATIC, EQUISPACED
• Default: AUTOMATIC
• In config_template.cfg: SPANWISE_KIND= 1
• Mentioned in: Setup Guide: Turbomachinery
• Code: CConfig.cpp line 1772

TURBOMACHINERY_KIND

types of turbomachinery architecture.

More in config_template.cfg: Specify kind of architecture for each zone (AXIAL, CENTRIPETAL, CENTRIFUGAL, CENTRIPETAL_AXIAL, AXIAL_CENTRIFUGAL)

• Type: list of the values below
• Values: AXIAL, CENTRIFUGAL, CENTRIPETAL, CENTRIPETAL_AXIAL, AXIAL_CENTRIFUGAL
• Default: AXIAL
• In config_template.cfg: TURBOMACHINERY_KIND= CENTRIPETAL CENTRIPETAL_AXIAL
• Mentioned in: Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 8 test case files, for example: circles.cfg (AXIAL AXIAL), transonic_stator.cfg (AXIAL), Jones_restart.cfg (CENTRIPETAL CENTRIPETAL_AXIAL)
• Code: CConfig.cpp line 1775

TURBO_PERF_KIND

types of turbomachynery Performance Calculations.

• Type: list of the values below
• Values: TURBINE, COMPRESSOR, PROPELLOR
• Default: TURBINE
• In config_template.cfg: TURBO_PERF_KIND = TURBINE TURBINE
• Mentioned in: Changes in Version 8, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 10 test case files, for example: circles.cfg (TURBINE TURBINE), transonic_stator.cfg (TURBINE), aachen_3D_MP_restart.cfg ((TURBINE, TURBINE, TURBINE))
• Code: CConfig.cpp line 1778

MARKER_SHROUD

markers in which velocity is forced to 0.0. Format: (shroud1, shroud2, …)

More in config_template.cfg: Shroud boundary marker(s) (NONE = no marker) Format: (marker) If the ROTATING_FRAME option is activated, this option force the velocity on the boundaries specified to 0.0

• Type: list of strings
• In config_template.cfg: MARKER_SHROUD= (NONE)
• Mentioned in: Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane
• Used in 2 test case files, for example: Arina2KRS.cfg ((NONE)), aachen_3D_MP_restart.cfg ((SHROUD1, SHROUD2, SHROUD3))
• Code: CConfig.cpp line 1781

MARKER_SUPERSONIC_INLET

Supersonic inlet boundary marker(s) Format: (inlet marker, temperature, static pressure, velocity_x, velocity_y, velocity_z, … ), i.e. primitive variables specified.

More in config_template.cfg: Supersonic inlet boundary marker(s) (NONE = no marker) Format: (inlet marker, temperature, static pressure, velocity_x, velocity_y, velocity_z, … ), i.e. primitive variables specified.

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_SUPERSONIC_INLET= ( NONE )
• Mentioned in: Markers and Boundary Conditions, Inviscid Supersonic Wedge
• Used in 15 test case files, for example: inv_wedge_ROE.cfg (( inlet, 300.0, 100000.0, 695.4290761824674, 0.0, 0.0 )), invwedge_ss_inlet.cfg (( Inlet, 288.15, 101325.0, 1705.16, 0.0, 0.0 )), NACA64206.cfg ((Inlet,216.6499,11662.0,472.1153,0,0))
• Code: CConfig.cpp line 1784

MARKER_SUPERSONIC_OUTLET

Supersonic outlet boundary marker(s)

More in config_template.cfg: Supersonic outlet boundary marker(s) (NONE = no marker)

• Type: list of strings
• In config_template.cfg: MARKER_SUPERSONIC_OUTLET= ( NONE )
• Used in 4 test case files, for example: flatplate_supersonic.cfg (( OUTLET )), NACA64206.cfg ((Outlet)), turb_SST_flatplate_compressibility_Sarkar.cfg ((outlet, 34384.76396))
• Code: CConfig.cpp line 1786

MARKER_OUTLET

Outlet boundary marker(s) Format: ( outlet marker, back pressure (static), … )

More in config_template.cfg: Outlet boundary marker(s) (NONE = no marker) Compressible: ( outlet marker, back pressure (static thermodynamic), … ) Inc. Pressure: ( outlet marker, back pressure (static gauge in Pa), … ) Inc. Mass Flow: ( outlet marker, mass flow target (kg/s), … )

• Type: list of (string, real number) pairs
• In config_template.cfg: MARKER_OUTLET= ( NONE )
• Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Turbomachinery, Setup Guide: Unsteady Flows and DES and 6 more
• Used in 114 test case files, for example: backwardStep.cfg (( OUTLET, 500.0 )), inv_wedge_ROE.cfg (( outlet, 10000.0 )), ddes_flatplate.cfg (( outlet, 115056.0, farfield, 115056.0 ))
• Code: CConfig.cpp line 1789

INC_OUTLET_TYPE

List of outlet types for incompressible flows. List length must match number of inlet markers. Options: PRESSURE_OUTLET, MASS_FLOW_OUTLET.

More in config_template.cfg: List of outlet types for incompressible flows. List length must match number of outlet markers. Options: PRESSURE_OUTLET, MASS_FLOW_OUTLET

• Type: list of the values below
• Values: PRESSURE_OUTLET, MASS_FLOW_OUTLET
• In config_template.cfg: INC_OUTLET_TYPE= PRESSURE_OUTLET
• Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Inviscid Hydrofoil, Turbulent Bend with wall functions
• Used in 50 test case files, for example: backwardStep.cfg (PRESSURE_OUTLET), inv_nozzle.cfg (MASS_FLOW_OUTLET), cylinder_split.cfg (( PRESSURE_OUTLET ))
• Code: CConfig.cpp line 1791

MARKER_ISOTHERMAL

Isothermal wall boundary marker(s) Format: ( isothermal marker, wall temperature (static), … )

More in config_template.cfg: Navier-Stokes (no-slip), isothermal wall marker(s) (NONE = no marker) Format: ( marker name, constant wall temperature (K), … )

• Type: list of (string, real number) pairs
• In config_template.cfg: MARKER_ISOTHERMAL= ( NONE )
• Mentioned in: Flamelet Solver — Python Wrapper Wall Boundary Conditions, Markers and Boundary Conditions, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics and 5 more
• Used in 48 test case files, for example: solid_cylinder1.cfg (( core1, 350.0 )), solid_cylinder2.cfg (( core2, 350.0 )), solid_cylinder3.cfg (( core3, 350.0 ))
• Code: CConfig.cpp line 1794

MARKER_HEATFLUX

Specified heat flux wall boundary marker(s) Format: ( Heat flux marker, wall heat flux (static), … )

More in config_template.cfg: Navier-Stokes (no-slip), constant heat flux wall marker(s) (NONE = no marker) Format: ( marker name, constant heat flux (J/m^2), … )

• Type: list of (string, real number) pairs
• In config_template.cfg: MARKER_HEATFLUX= ( NONE )
• Mentioned in: Flamelet Solver — Python Wrapper Wall Boundary Conditions, Markers and Boundary Conditions, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Non-Ideal Compressible Flows and 14 more
• Used in 183 test case files, for example: air_nozzle_restart.cfg (( WALL, 0.0 )), backwardStep.cfg (( WALL_TOP, 0.0, WALL_BOTTOM, 0.0 )), config.cfg (( OuterWall, 0.0, InnerWall, 0.0 ))
• Code: CConfig.cpp line 1797

INTEGRATED_HEATFLUX

Prescribe Heatflux in [W] instead of [W/m^2] \default false

• Type: YES / NO
• Default: NO
• Not in config_template.cfg.
• Mentioned in: Markers and Boundary Conditions, Setup Guide: Heat Transfer and Conjugate Heat Transfer
• Used in 1 test case file, for example: configSolid.cfg (YES)
• Code: CConfig.cpp line 1799

MARKER_HEATTRANSFER

Heat flux with specified heat transfer coefficient boundary marker(s) Format: ( Heat transfer marker, heat transfer coefficient, wall temperature (static), … )

More in config_template.cfg: Navier-Stokes (no-slip), heat-transfer/convection wall marker(s) (NONE = no marker) Available for compressible and incompressible flow. Format: ( marker name, constant heat-transfer coefficient (J/(K*m^2)), constant reservoir Temperature (K) … )

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_HEATTRANSFER= ( NONE )
• Mentioned in: Markers and Boundary Conditions, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Wall Treatment: Wall Functions and Roughness
• Used in 1 test case file, for example: BC_HeatTransfer.cfg (( fluid_pin1_interface, 100000000.0, 400, \)
• Code: CConfig.cpp line 1802

MARKER_SMOLUCHOWSKI_MAXWELL

moluchowski/Maxwell wall boundary marker(s) Slip velocity and temperature jump wall boundary marker(s) Format: ( Heat flux marker, wall temperature (static), momentum accomodation coefficient, thermal accomodation coefficient … )

More in config_template.cfg: Smoluchowski/Maxwell slip wall boundary marker(s)

• Type: list of (string, real number) pairs
• In config_template.cfg: MARKER_SMOLUCHOWSKI_MAXWELL= ( NONE )
• Code: CConfig.cpp line 1805

WALL_ROUGHNESS

Specified roughness heights at wall boundary marker(s) Format: ( Wall marker, roughness_height (static), … )

More in config_template.cfg: The equivalent sand grain roughness height (k_s) on each of the wall. This must be in m. This is a list of (string, double) each element corresponding to a wall marker.

• Type: list of (string, real number) pairs
• In config_template.cfg: WALL_ROUGHNESS = (wall1, ks1, wall2, ks2)
• Mentioned in: Changes in Version 8, Hybrid RANS/LES (DES), Setup Guide: Steady RANS for External Aerodynamics, Wall Treatment: Wall Functions and Roughness
• Used in 5 test case files, for example: pb_rough_flatplate_incomp.cfg ((wall, 0.000246)), turb_SST_flatplate_roughBCAupoix.cfg ((wall, 400e-6))
• Code: CConfig.cpp line 1808

MARKER_ENGINE_INFLOW

Engine inflow boundary marker(s) Format: ( nacelle inflow marker, fan face Mach, … )

More in config_template.cfg: Engine inflow boundary marker(s) (NONE = no marker) Format: (engine inflow marker, fan face Mach, … )

• Type: list of (string, real number) pairs
• In config_template.cfg: MARKER_ENGINE_INFLOW= ( NONE )
• Used in 1 test case file, for example: MFR_coupling.cfg (( FAN_IN, 140.0 ))
• Code: CConfig.cpp line 1811

HIGHLITE_AREA

Highlite area

More in config_template.cfg: Highlite area to compute MFR (1 in2 by default)

• Type: real number
• Default: 1.0
• In config_template.cfg: HIGHLITE_AREA= 1.0
• Used in 3 test case files, for example: actuatordisk_bem.cfg (0.04411429), propeller_variable_load.cfg (19.8649), propeller.cfg (1.0)
• Code: CConfig.cpp line 1813

FAN_POLY_EFF

Fan poly efficiency

More in config_template.cfg: Fan polytropic efficiency (1.0 by default)

• Type: real number
• Default: 1.0
• In config_template.cfg: FAN_POLY_EFF= 1.0
• Code: CConfig.cpp line 1815

SUBSONIC_ENGINE

Engine subsonic intake region

More in config_template.cfg: Initialization with a subsonic flow around the engine.

• Type: YES / NO
• Default: NO
• In config_template.cfg: SUBSONIC_ENGINE= NO
• Code: CConfig.cpp line 1817

ACTDISK_DOUBLE_SURFACE

Actuator disk double surface

• Type: YES / NO
• Default: NO
• In config_template.cfg: ACTDISK_DOUBLE_SURFACE= NO
• Mentioned in: Actuator Disk With Variable Load
• Used in 2 test case files, for example: actuatordisk_bem.cfg (YES)
• Code: CConfig.cpp line 1819

BEM_PROP_BLADE_ANGLE

Propeller blade angle for actuator disk BEM.

More in config_template.cfg: Propeller blade angle (degrees) at (0.75 * radius)

• Type: real number
• Default: 23.9
• In config_template.cfg: BEM_PROP_BLADE_ANGLE = 25.0
• Used in 1 test case file, for example: actuatordisk_bem.cfg (23.9)
• Code: CConfig.cpp line 1822

BEM_PROP_FILENAME

Propeller file name for actuator disk BEM.

More in config_template.cfg: Propeller blade element section and aerodynamic data input file name

• Type: string
• Default: string("prop_geom_alfclcd_data.txt")
• In config_template.cfg: BEM_PROP_FILENAME = prop_geom_alfclcd_data.txt
• Used in 1 test case file, for example: actuatordisk_bem.cfg (prop_geom_alfclcd_data.txt)
• Code: CConfig.cpp line 1824

BEM_FREQ

Frequency for updating actuator disk with BEM.

More in config_template.cfg: BEM calculation frequency

• Type: integer
• Default: 40
• In config_template.cfg: BEM_FREQ = 40
• Used in 1 test case file, for example: actuatordisk_bem.cfg (40)
• Code: CConfig.cpp line 1826

ENGINE_HALF_MODEL

Only half engine is in the computational grid

More in config_template.cfg: Only half engine is in the computational grid (NO, YES)

• Type: YES / NO
• Default: NO
• In config_template.cfg: ENGINE_HALF_MODEL= NO
• Code: CConfig.cpp line 1829

ACTDISK_SU2_DEF

Actuator disk SU2_DEF

• Type: YES / NO
• Default: NO
• Not in config_template.cfg.
• Code: CConfig.cpp line 1831

DISTORTION_RACK

Definition of the distortion rack (radial number of proves / circumferential density (degree)

• Type: fixed-size list of real numbers
• Default: Not extracted; see the code.
• In config_template.cfg: DISTORTION_RACK= (0.0, 0.0)
• Code: CConfig.cpp line 1834

SUBSONIC_ENGINE_VALUES

Values of the box to impose a subsonic nacellle (mach, Pressure, Temperature)

More in config_template.cfg: Flow variables that define the subsonic region (Mach, Alpha, Beta, Pressure, Temperature)

• Type: fixed-size list of real numbers
• Default: Not extracted; see the code.
• In config_template.cfg: SUBSONIC_ENGINE_VALUES= ( 0.4, 0.0, 0.0, 2116.216, 518.67 )
• Code: CConfig.cpp line 1837

SUBSONIC_ENGINE_CYL

Coordinates of the box to impose a subsonic nacellle cylinder (Xmin, Ymin, Zmin, Xmax, Ymax, Zmax, Radius)

More in config_template.cfg: Axis of the cylinder that defines the subsonic region (A_X, A_Y, A_Z, B_X, B_Y, B_Z, Radius)

• Type: fixed-size list of real numbers
• Default: Not extracted; see the code.
• In config_template.cfg: SUBSONIC_ENGINE_CYL= ( 0.0, 0.0, 0.0, 1.0, 0.0 , 0.0, 1.0 )
• Code: CConfig.cpp line 1841

MARKER_ENGINE_EXHAUST

Engine exhaust boundary marker(s) Format: (nacelle exhaust marker, total nozzle temp, total nozzle pressure, … )

More in config_template.cfg: Engine exhaust boundary marker(s) with the following formats (NONE = no marker) Format: (engine exhaust marker, total nozzle temp, total nozzle pressure, … )

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_ENGINE_EXHAUST= ( NONE )
• Used in 1 test case file, for example: MFR_coupling.cfg (( FAN_OUT, 289.761088684333, 103321.726628227, CORE_OUT, 289.761088684333, 103321.726628227 ))
• Code: CConfig.cpp line 1844

MARKER_CLAMPED

Clamped boundary marker(s)

• Type: list of strings
• In config_template.cfg: MARKER_CLAMPED= ( NONE )
• Mentioned in: Markers and Boundary Conditions, Linear Elasticity, Non-linear Elasticity
• Used in 24 test case files, for example: configAD_fem.cfg (( Clamped )), configFEA.cfg (( clamped )), configFEA.cfg (( Clamped_Right, Clamped_Left ))
• Code: CConfig.cpp line 1846

MARKER_NORMAL_DISPL

Displacement boundary marker(s)

More in config_template.cfg: Displacement boundary marker(s) (NONE = no marker) Format: ( displacement marker, displacement value normal to the surface, … )

• Type: list of (string, real number) pairs
• In config_template.cfg: MARKER_NORMAL_DISPL= ( NONE )
• Code: CConfig.cpp line 1848

MARKER_PRESSURE

Load boundary marker(s) - uniform pressure in Pa

More in config_template.cfg: Pressure boundary marker(s) (NONE = no marker) Format: ( pressure marker )

• Type: list of (string, real number) pairs
• In config_template.cfg: MARKER_PRESSURE= ( NONE )
• Mentioned in: Markers and Boundary Conditions, Linear Elasticity, Non-linear Elasticity
• Used in 17 test case files, for example: configAD_fem.cfg (( LowerBeamS, 0.0, UpperBeamS, 1.00, RightBeamS, 0.0)), configBeam_2d.cfg (( lower, 0 )), config.cfg (( RightBeamS , 0, LowerBeamS, 0, UpperBeamS, 0))
• Code: CConfig.cpp line 1850

MARKER_DAMPER

Load boundary marker(s)

• Type: list of (string, real number) pairs
• In config_template.cfg: MARKER_DAMPER= ( NONE )
• Code: CConfig.cpp line 1852

MARKER_LOAD

Load boundary marker(s) Format: (inlet marker, load, multiplier, dir_x, dir_y, dir_z, … ), i.e. primitive variables specified.

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_LOAD= ( NONE )
• Mentioned in: Markers and Boundary Conditions, Linear Elasticity
• Used in 12 test case files, for example: configBeam_2d.cfg (( upper, 1, 1000, 0, -1, 0 )), config.cfg (( load,1,0.1,1,0,0 )), linear_plane_strain_2d.cfg (( x_plus, 1, 1000, 0, -1, 0 ))
• Code: CConfig.cpp line 1855

MARKER_DISPLACEMENT

Load boundary marker(s) Format: (inlet marker, load, multiplier, dir_x, dir_y, dir_z, … ), i.e. primitive variables specified.

• Type: special format, see config_template.cfg
• In config_template.cfg: MARKER_DISPLACEMENT= ( NONE )
• Mentioned in: Markers and Boundary Conditions
• Code: CConfig.cpp line 1858

SINE_LOAD

option to apply the load as a sine

• Type: YES / NO
• Default: NO
• In config_template.cfg: SINE_LOAD= NO
• Mentioned in: Linear Dynamics
• Code: CConfig.cpp line 1860

SINE_LOAD_COEFF

the 1st coeff is the amplitude, the 2nd is the frequency, 3rd is the phase in radians

More in config_template.cfg: the 1st coeff is the amplitude, the 2nd is the frequency, the 3rd is the phase in radians

• Type: fixed-size list of real numbers
• Default: Not extracted; see the code.
• In config_template.cfg: SINE_LOAD_COEFF= (0.0, 0.0, 0.0)
• Mentioned in: Linear Dynamics
• Code: CConfig.cpp line 1863

RAMP_AND_RELEASE_LOAD

release the load after applying the ramp

• Type: YES / NO
• Default: NO
• In config_template.cfg: RAMP_AND_RELEASE_LOAD= NO
• Code: CConfig.cpp line 1865

BC_EVAL_FREQ

Evaluation frequency for Engine and Actuator disk markers.

• Type: integer
• Default: 40
• In config_template.cfg: BC_EVAL_FREQ = 40
• Code: CConfig.cpp line 1868

DAMP_ENGINE_INFLOW

Damping factor for engine inlet condition

More in config_template.cfg: Damping factor for the engine inflow.

• Type: real number
• Default: 0.95
• In config_template.cfg: DAMP_ENGINE_INFLOW= 0.95
• Used in 1 test case file, for example: MFR_coupling.cfg (0.01)
• Code: CConfig.cpp line 1870

DAMP_ENGINE_EXHAUST

Damping factor for engine exhaust condition

More in config_template.cfg: Damping factor for the engine exhaust.

• Type: real number
• Default: 0.95
• In config_template.cfg: DAMP_ENGINE_EXHAUST= 0.95
• Code: CConfig.cpp line 1872

ENGINE_INFLOW_TYPE

Inlet boundary type

More in config_template.cfg: Engine Inflow boundary type (FAN_FACE_MACH, FAN_FACE_PRESSURE, FAN_FACE_MDOT)

• Type: one of the values below
• Values: FAN_FACE_MACH, FAN_FACE_MDOT, FAN_FACE_PRESSURE
• Default: FAN_FACE_MACH
• In config_template.cfg: ENGINE_INFLOW_TYPE= FAN_FACE_MACH
• Used in 1 test case file, for example: MFR_coupling.cfg (FAN_FACE_MDOT)
• Code: CConfig.cpp line 1874

ENGINE

Evaluate a problem with engines

• Type: YES / NO
• Default: NO
• In config_template.cfg: ENGINE= NO
• Code: CConfig.cpp line 1876

ENGINE_EXHAUST_TO_INLET

Use exhaust mass flow as inlet mass flow.

More in config_template.cfg: Flag to allow mass-flow rate coupling between all exhaust surfaces and the engine inlet (YES, NO)

• Type: YES / NO
• Default: NO
• In config_template.cfg: ENGINE_EXHAUST_TO_INLET= NO
• Mentioned in: Changes in Version 8
• Used in 1 test case file, for example: MFR_coupling.cfg (YES)
• Code: CConfig.cpp line 1878

BUFFET_K

Sharpness coefficient for the buffet sensor

More in config_template.cfg: Sharpness coefficient for the buffet sensor Heaviside function

• Type: real number
• Default: 10.0
• In config_template.cfg: BUFFET_K= 10.0
• Code: CConfig.cpp line 1881

BUFFET_LAMBDA

Offset parameter for the buffet sensor

More in config_template.cfg: Offset parameter for the buffet sensor Heaviside function

• Type: real number
• Default: 0.0
• In config_template.cfg: BUFFET_LAMBDA= 0.0
• Code: CConfig.cpp line 1883

NEWTON_KRYLOV

Use a Newton-Krylov method.

More in config_template.cfg: Use a Newton-Krylov method on the flow equations, see TestCases/rans/oneram6/turb_ONERAM6_nk.cfg For multizone discrete adjoint it will use FGMRES on inner iterations with restart frequency equal to “QUASI_NEWTON_NUM_SAMPLES”.

• Type: YES / NO
• Default: NO
• In config_template.cfg: NEWTON_KRYLOV= NO
• Mentioned in: Setup Guide: Steady RANS for External Aerodynamics
• Used in 9 test case files, for example: configFlow.cfg (YES), config_sst.cfg (NO)
• Code: CConfig.cpp line 1886

NEWTON_KRYLOV_IPARAM

Integer parameters {startup iters, precond iters, initial tolerance relaxation}.

• Type: fixed-size list of integers
• Default: Not extracted; see the code.
• In config_template.cfg: NEWTON_KRYLOV_IPARAM= (20, 3, 2)
• Used in 6 test case files, for example: inv_ramp.cfg ((0, 1, 1)), inv_ramp_msw.cfg ((0, 0, 1)), turb_ONERAM6_nk.cfg ((200, 0, 1))
• Code: CConfig.cpp line 1888

NEWTON_KRYLOV_DPARAM

Double parameters {startup residual drop, precond tolerance, full tolerance residual drop, findiff step, NK relaxation}.

More in config_template.cfg: Double parameters {startup residual drop, precond tolerance, full tolerance residual drop, findiff step, and MUSCL relaxation for the finite difference products}.

• Type: fixed-size list of real numbers
• Default: Not extracted; see the code.
• In config_template.cfg: NEWTON_KRYLOV_DPARAM= (-2.0, 0.1, -6.0, 1e-5, 1.0)
• Used in 6 test case files, for example: inv_ramp.cfg ((0.0, 1e-20, -2.0, 1e-5, 1.0)), inv_ramp_msw.cfg ((0, 1e-20, -2.0, 1e-5, -1.0)), turb_ONERAM6_nk.cfg ((0, 0, 0, 1e-5, -1))
• Code: CConfig.cpp line 1890

QUASI_NEWTON_NUM_SAMPLES

Number of samples for quasi-Newton methods.

More in config_template.cfg: Enable (if != 0) quasi-Newton acceleration/stabilization of discrete adjoints

• Type: integer
• Default: 0
• In config_template.cfg: QUASI_NEWTON_NUM_SAMPLES= 20
• Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint
• Used in 6 test case files, for example: configFlow.cfg (999), turb_naca0012_sst.cfg (30), transonic_stator.cfg (20)
• Code: CConfig.cpp line 1893

USE_VECTORIZATION

Whether to use vectorized numerical schemes, less robust against transients.

More in config_template.cfg: Use the vectorized version of the selected numerical method (available for JST family and Roe). SU2 should be compiled for an AVX or AVX512 architecture for best performance. NOTE: Currently vectorization always used for schemes that support it.

• Type: YES / NO
• Default: NO
• In config_template.cfg: USE_VECTORIZATION= YES
• Mentioned in: Setup Guide: Laminar-Turbulent Transition
• Used in 1 test case file, for example: config.cfg (YES)
• Code: CConfig.cpp line 1895