Freestream Conditions

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.

GAS_CONSTANT

Specific gas constant (287.058 J/kg*K (air), only for compressible flows)

More in config_template.cfg: Specific gas constant (287.058 J/kg*K default and this value is hardcoded for the model STANDARD_AIR, compressible only)

Type: real number
Default: 287.058
In config_template.cfg: GAS_CONSTANT= 287.058
Mentioned in: Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Turbomachinery, Non-ideal compressible flow in a supersonic nozzle, Turbulent ONERA M6
Used in 87 test case files, for example: inv_ONERAM6_moving.cfg (287.058), def_brick_hex.cfg (287.87), Arina2KRS.cfg (518.28)
Code: CConfig.cpp line 1307

GAMMA_VALUE

Ratio of specific heats (1.4 (air), only for compressible flows)

More in config_template.cfg: Ratio of specific heats (1.4 default and the value is hardcoded for the model STANDARD_AIR, compressible only)

Type: real number
Default: 1.4
In config_template.cfg: GAMMA_VALUE= 1.4
Mentioned in: Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Turbomachinery, Non-ideal compressible flow in a supersonic nozzle, Turbulent ONERA M6
Used in 87 test case files, for example: inv_ONERAM6_moving.cfg (1.4), Arina2KRS.cfg (1.338), transonic_stator.cfg (1.0165)
Code: CConfig.cpp line 1309

THERMODYNAMIC_PRESSURE

Thermodynamics(operating) Pressure (101325 Pa), only for incompressible flows)

More in config_template.cfg: Thermodynamics(operating) Pressure (101325 Pa default value, only for incompressible flow and FLUID_MIXTURE)

Type: real number
Default: 101325.0
In config_template.cfg: THERMODYNAMIC_PRESSURE= 101325.0
Mentioned in: Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations
Used in 13 test case files, for example: laminar_premixed_h2_flame_cfd.cfg (101325), active_species_transport_temp_limits.cfg (101325.0)
Code: CConfig.cpp line 1311

SPECIFIC_HEAT_CP

Specific heat at constant pressure, Cp (1004.703 J/kg*K (air), constant density incompressible fluids only)

More in config_template.cfg: Specific heat at constant pressure, Cp (1004.703 J/kg*K (air)). Incompressible fluids with energy eqn. (CONSTANT_DENSITY, INC_IDEAL_GAS) and the heat equation.

Type: list of real numbers
In config_template.cfg: SPECIFIC_HEAT_CP= 1004.703
Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Laminar Buoyancy-driven Cavity, Laminar Flat Plate with Heat Transfer and 1 more
Used in 65 test case files, for example: solid_cylinder1.cfg (1004.703), fluid.cfg (4180), solid.cfg (0.8710)
Code: CConfig.cpp line 1313

THERMAL_EXPANSION_COEFF

Thermal expansion coefficient (0.00347 K^-1 (air), used for Boussinesq approximation for liquids/non-ideal gases)

More in config_template.cfg: Thermal expansion coefficient (0.00347 K^-1 (air)) Used with Boussinesq approx. (incompressible, BOUSSINESQ density model only)

Type: real number
Default: 0.00347
In config_template.cfg: THERMAL_EXPANSION_COEFF= 0.00347
Mentioned in: Setup Guide: Incompressible Flows
Used in 2 test case files, for example: turb_SST_flatplate_compressibility_Sarkar.cfg (0.00347)
Code: CConfig.cpp line 1315

MOLECULAR_WEIGHT

Molecular weight for an incompressible ideal gas (28.96 g/mol (air) default)

More in config_template.cfg: Molecular Weights of species for an incompressible ideal gas (28.96 g/mol (air) default), For multispecies, we have N Molecular weights: W_1, W_2,…., W_N

Type: list of real numbers
In config_template.cfg: MOLECULAR_WEIGHT= 28.96, 16.043
Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Laminar Buoyancy-driven Cavity
Used in 33 test case files, for example: flow_cylinder.cfg (28.96), turb_SA_flatplate_species.cfg (28.960), zone1.cfg ((28.96, 25.0, 20.0))
Code: CConfig.cpp line 1317

GAS_MODEL

Specify chemical model for multi-species simulations - read by Mutation++ library

More in config_template.cfg: Gas model - mixture

Type: string
Default: string("N2")
In config_template.cfg: GAS_MODEL= AIR-5
Mentioned in: Physical Definition
Used in 15 test case files, for example: invwedge_am.cfg (AIR-5), thermalbath.cfg (N2), weakly_ionized.cfg (AIR-7)
Code: CConfig.cpp line 1322

TRANSPORT_COEFF_MODEL

Specify transport coefficient model for multi-species simulations

More in config_template.cfg: Mixture transport properties (WILKE,GUPTA-YOS,CHAPMANN-ENSKOG, SUTHERLAND)

Type: one of the values below
Values: SUTHERLAND, WILKE, GUPTA-YOS, CHAPMANN-ENSKOG
Default: WILKE
In config_template.cfg: TRANSPORT_COEFF_MODEL = WILKE
Mentioned in: Physical Definition
Used in 1 test case file, for example: cyl_ion_gy.cfg (GUPTA-YOS)
Code: CConfig.cpp line 1324

GAS_COMPOSITION

Specify mass fraction of each species

More in config_template.cfg: Initial gas composition in mass fractions

Type: list of real numbers
In config_template.cfg: GAS_COMPOSITION= (0.77, 0.23, 0.0, 0.0, 0.0)
Mentioned in: Physical Definition
Used in 15 test case files, for example: invwedge_am.cfg ((0.77, 0.23, 0.0, 0.0, 0.0)), thermalbath.cfg ((0.666667, 0.333333)), weakly_ionized.cfg ((0.0, 0.767, 0.233, 0.0, 0.0, 0.0, 0.0))
Code: CConfig.cpp line 1326

INLET_GAS_COMPOSITION

Specify mass fraction of each species for NEMO inlet

Type: list of real numbers
In config_template.cfg: INLET_GAS_COMPOSITION = (0.77, 0.23, 0.0, 0.0, 0.0)
Mentioned in: Markers and Boundary Conditions
Used in 1 test case file, for example: invwedge_ss_inlet.cfg ((0.77, 0.23, 0.0, 0.0, 0.0))
Code: CConfig.cpp line 1328

INLET_TEMPERATURE_VE

NEMO inlet temperature_ve (K), if left 0 K, set to Ttr value

More in config_template.cfg: NEMO Inlet Options

Type: real number
Default: 0.0
In config_template.cfg: INLET_TEMPERATURE_VE = 288.15
Mentioned in: Markers and Boundary Conditions
Used in 1 test case file, for example: invwedge_ss_inlet.cfg (288.15)
Code: CConfig.cpp line 1330

FROZEN_MIXTURE

Specify if mixture is frozen

More in config_template.cfg: Freeze chemical reactions

Type: YES / NO
Default: NO
In config_template.cfg: FROZEN_MIXTURE= NO
Used in 1 test case file, for example: thermalbath_frozen.cfg (YES)
Code: CConfig.cpp line 1332

IONIZATION

Specify if there is ionization

Type: YES / NO
Default: NO
In config_template.cfg: IONIZATION= NO
Code: CConfig.cpp line 1334

VT_RESIDUAL_LIMITING

Specify if there is VT transfer residual limiting

Type: YES / NO
Default: NO
In config_template.cfg: VT_RESIDUAL_LIMITING= NO
Code: CConfig.cpp line 1336

CATALYTIC_WALL

List of catalytic walls

More in config_template.cfg: Catalytic wall marker(s) (NONE = no marker) Format: ( marker name, … )

Type: list of strings
In config_template.cfg: CATALYTIC_WALL= ( NONE )
Used in 2 test case files, for example: partial_cat.cfg ((wall))
Code: CConfig.cpp line 1338

SUPERCATALYTIC_WALL

Specfify super-catalytic wall

More in config_template.cfg: specify if catalytic wall is a supercatalytic wall

Type: YES / NO
Default: NO
In config_template.cfg: SUPERCATALYTIC_WALL= NO
Used in 2 test case files, for example: partial_cat.cfg (NO), super_cat.cfg (YES)
Code: CConfig.cpp line 1340

SUPERCATALYTIC_WALL_COMPOSITION

Wall mass fractions for supercatalytic case

More in config_template.cfg: species composition at the supercatalytic wall

Type: list of real numbers
In config_template.cfg: SUPERCATALYTIC_WALL_COMPOSITION= (0,0,0)
Used in 1 test case file, for example: super_cat.cfg ((0.77, 0.23, 0.0, 0.0, 0.0))
Code: CConfig.cpp line 1342

CATALYTIC_EFFICIENCY

Specfify catalytic efficiency of wall if using gamma model

Type: real number
Default: 1.0
In config_template.cfg: CATALYTIC_EFFICIENCY= 0.2
Used in 1 test case file, for example: partial_cat.cfg (0.2)
Code: CConfig.cpp line 1344

CRITICAL_TEMPERATURE

Critical Temperature, default value for AIR

More in config_template.cfg: Critical Temperature (131.00 K by default)

Type: real number
Default: 131.00
In config_template.cfg: CRITICAL_TEMPERATURE= 131.00
Mentioned in: Setup Guide: Non-Ideal Compressible Flows, Non-ideal compressible flow in a supersonic nozzle
Used in 15 test case files, for example: Arina2KRS.cfg (190.564), transonic_stator.cfg (564.1), unsteady_CHT_FlatPlate_Conf.cfg (131.00)
Code: CConfig.cpp line 1350

CRITICAL_PRESSURE

Critical Pressure, default value for MDM

More in config_template.cfg: Critical Pressure (3588550.0 N/m^2 by default)

Type: real number
Default: 3588550.0
In config_template.cfg: CRITICAL_PRESSURE= 3588550.0
Mentioned in: Setup Guide: Non-Ideal Compressible Flows, Non-ideal compressible flow in a supersonic nozzle
Used in 15 test case files, for example: Arina2KRS.cfg (4599200.0), transonic_stator.cfg (1415000.0), turb_SA_PR.cfg (1415000)
Code: CConfig.cpp line 1352

CRITICAL_DENSITY

Critical Density, default value for MDM

More in config_template.cfg: Critical Density (263.0 kg/m^3 by default)

Type: real number
Default: 263.0
In config_template.cfg: CRITICAL_DENSITY= 263.0
Mentioned in: Setup Guide: Non-Ideal Compressible Flows
Used in 8 test case files, for example: turb_SA_PR.cfg (256.74), edge_PPR.cfg (256.82), turb_NACA0012_sst_multigrid_restart.cfg (263.0)
Code: CConfig.cpp line 1354

ACENTRIC_FACTOR

Critical Density, default value for MDM

More in config_template.cfg: Acentric factor (0.035 (air))

Type: real number
Default: 0.035
In config_template.cfg: ACENTRIC_FACTOR= 0.035
Mentioned in: Setup Guide: Non-Ideal Compressible Flows, Non-ideal compressible flow in a supersonic nozzle
Used in 18 test case files, for example: Arina2KRS.cfg (0.01142), transonic_stator.cfg (0.529), unsteady_CHT_FlatPlate_Conf.cfg (0.035)
Code: CConfig.cpp line 1358

VISCOSITY_MODEL

model of the viscosity

More in config_template.cfg: Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY, POLYNOMIAL_VISCOSITY, FLAMELET).

Type: one of the values below
Values: CONSTANT_VISCOSITY, SUTHERLAND, POLYNOMIAL_VISCOSITY, FLAMELET, COOLPROP
Default: SUTHERLAND
In config_template.cfg: VISCOSITY_MODEL= SUTHERLAND
Mentioned in: Physical Definition, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics and 8 more
Used in 134 test case files, for example: air_nozzle_restart.cfg (CONSTANT_VISCOSITY), heated_cylinder.cfg (SUTHERLAND), lam_prem_ch4_cfd.cfg (FLAMELET)
Code: CConfig.cpp line 1362

MU_CONSTANT

default value for AIR

More in config_template.cfg: Molecular Viscosity that would be constant (1.716E-5 by default)

Type: list of real numbers
In config_template.cfg: MU_CONSTANT= 1.716E-5
Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Laminar Buoyancy-driven Cavity and 2 more
Used in 109 test case files, for example: air_nozzle_restart.cfg (1.716E-5), backwardStep.cfg (1.820E-5), flow_cylinder.cfg (1.7893e-05)
Code: CConfig.cpp line 1367

MU_REF

Sutherland Viscosity Ref default value for AIR SI

More in config_template.cfg: Sutherland Viscosity Ref (1.716E-5 default value for AIR SI)

Type: list of real numbers
In config_template.cfg: MU_REF= 1.716E-5
Mentioned in: Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Turbomachinery, Composition-Dependent model for Species Transport equations, Turbulent ONERA M6
Used in 42 test case files, for example: flow_cylinder.cfg (1.716E-5), psi.cfg (1.716e-5), configp1adjoint.cfg (1.0E-5)
Code: CConfig.cpp line 1372

MU_T_REF

Sutherland Temperature Ref, default value for AIR SI

More in config_template.cfg: Sutherland Temperature Ref (273.15 K default value for AIR SI)

Type: list of real numbers
In config_template.cfg: MU_T_REF= 273.15
Mentioned in: Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Turbomachinery, Composition-Dependent model for Species Transport equations, Turbulent ONERA M6
Used in 42 test case files, for example: flow_cylinder.cfg (273.15), turb_SA_PR.cfg (288.15), configp1adjoint.cfg (300.0)
Code: CConfig.cpp line 1374

SUTHERLAND_CONSTANT

Sutherland constant, default value for AIR SI

More in config_template.cfg: Sutherland constant (110.4 default value for AIR SI)

Type: list of real numbers
In config_template.cfg: SUTHERLAND_CONSTANT= 110.4
Mentioned in: Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Turbomachinery, Composition-Dependent model for Species Transport equations, Turbulent ONERA M6
Used in 42 test case files, for example: flow_cylinder.cfg (110.4), active_species_transport_temp_limits.cfg (97, 111), species2_primitiveVenturi_mixingmodel_viscosity.cfg (129.4, 187.78)
Code: CConfig.cpp line 1376

MIXING_VISCOSITY_MODEL

Mixing model of the viscosity

More in config_template.cfg: mixing model for species transport (DAVIDSON, WILKE)

Type: one of the values below
Values: WILKE, DAVIDSON
Default: DAVIDSON
In config_template.cfg: MIXING_VISCOSITY_MODEL= DAVIDSON
Mentioned in: Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations
Used in 9 test case files, for example: zone1.cfg (WILKE), species2_primitiveVenturi_mixingmodel_TURBULENT_MARKERS.cfg (DAVIDSON)
Code: CConfig.cpp line 1380

CONDUCTIVITY_MODEL

Laminar Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL, POLYNOMIAL_CONDUCTIVITY, FLAMELET). (from config_template.cfg)

Type: one of the values below
Values: CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL, POLYNOMIAL_CONDUCTIVITY, FLAMELET, COOLPROP
Default: CONSTANT_PRANDTL
In config_template.cfg: CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
Mentioned in: Changes in Version 8, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics and 7 more
Used in 82 test case files, for example: air_nozzle_restart.cfg (CONSTANT_PRANDTL), transonic_stator.cfg (CONSTANT_CONDUCTIVITY), lam_prem_ch4_cfd.cfg (FLAMELET)
Code: CConfig.cpp line 1384

TURBULENT_CONDUCTIVITY_MODEL

Definition of the turbulent thermal conductivity model (CONSTANT_PRANDTL_TURB (default), NONE).

More in config_template.cfg: Definition of the turbulent thermal conductivity model for RANS (CONSTANT_PRANDTL_TURB by default, NONE).

Type: one of the values below
Values: NONE, CONSTANT_PRANDTL_TURB
Default: CONSTANT_PRANDTL_TURB
In config_template.cfg: TURBULENT_CONDUCTIVITY_MODEL= CONSTANT_PRANDTL_TURB
Mentioned in: Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Turbulence Models, Composition-Dependent model for Species Transport equations
Used in 29 test case files, for example: pb_poly_cylinder.cfg (CONSTANT_PRANDTL_TURB), zone1.cfg (NONE)
Code: CConfig.cpp line 1387

THERMAL_CONDUCTIVITY_CONSTANT

default value for AIR

More in config_template.cfg: Thermal conductivity used for heat equation

Type: list of real numbers
In config_template.cfg: THERMAL_CONDUCTIVITY_CONSTANT= 0.0
Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Laminar Buoyancy-driven Cavity and 2 more
Used in 64 test case files, for example: solid_cylinder1.cfg (0.1028), flow_cylinder.cfg (0.0257), solid.cfg (200)
Code: CConfig.cpp line 1392

CP_POLYCOEFFS

Definition of the temperature polynomial coefficients for specific heat Cp.

More in config_template.cfg: Temperature polynomial coefficients (up to quartic) for specific heat Cp. Format -> Cp(T) : b0 + b1T + b2T^2 + b3T^3 + b4T^4

Type: fixed-size list of real numbers
Default: Not extracted; see the code.
In config_template.cfg: CP_POLYCOEFFS= (0.0, 0.0, 0.0, 0.0, 0.0)
Mentioned in: Setup Guide: Incompressible Flows
Used in 3 test case files, for example: pb_poly_cylinder.cfg (( 1004.703, 0.1, 0.0, 0.0, 0.0))
Code: CConfig.cpp line 1397

MU_POLYCOEFFS

Definition of the temperature polynomial coefficients for specific heat Cp.

More in config_template.cfg: Temperature polynomial coefficients (up to quartic) for viscosity. Format -> Mu(T) : b0 + b1T + b2T^2 + b3T^3 + b4T^4

Type: fixed-size list of real numbers
Default: Not extracted; see the code.
In config_template.cfg: MU_POLYCOEFFS= (0.0, 0.0, 0.0, 0.0, 0.0)
Mentioned in: Setup Guide: Incompressible Flows
Used in 4 test case files, for example: pb_poly_cylinder.cfg ((1.7893e-05, 1e-8, 0.0, 0.0, 0.0)), psi.cfg ((1.097e-5, 3.437e-8, 3.332e-12, 0, 0))
Code: CConfig.cpp line 1399

KT_POLYCOEFFS

Definition of the temperature polynomial coefficients for specific heat Cp.

More in config_template.cfg: Temperature polynomial coefficients (up to quartic) for conductivity. Format -> Kt(T) : b0 + b1T + b2T^2 + b3T^3 + b4T^4

Type: fixed-size list of real numbers
Default: Not extracted; see the code.
In config_template.cfg: KT_POLYCOEFFS= (0.0, 0.0, 0.0, 0.0, 0.0)
Mentioned in: Setup Guide: Incompressible Flows
Used in 3 test case files, for example: pb_poly_cylinder.cfg ((0.0257, 1e-5, 0.0, 0.0, 0.0))
Code: CConfig.cpp line 1401

REYNOLDS_NUMBER

Reynolds number (non-dimensional, based on the free-stream values). Needed for viscous solvers. For incompressible solvers the Reynolds length will always be 1.0

Type: real number
Default: 0.0
In config_template.cfg: REYNOLDS_NUMBER= 6.5E6
Mentioned in: Physical Definition, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Unsteady Flows and DES, Turbulent ONERA M6
Used in 118 test case files, for example: config.cfg (3.28E6), lam_cylinder.cfg (40.0), lam_NACA0012.cfg (3000.0)
Code: CConfig.cpp line 1404

REYNOLDS_LENGTH

Reynolds length (1 m by default). Used for compressible solver: incompressible solver will use 1.0.

More in config_template.cfg: Reynolds length (1 m, 1 inch by default)

Type: real number
Default: 1.0
In config_template.cfg: REYNOLDS_LENGTH= 1.0
Mentioned in: Hybrid RANS/LES (DES), Setup Guide: Laminar-Turbulent Transition, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Unsteady Flows and DES, Turbulent ONERA M6
Used in 116 test case files, for example: backwardStep.cfg (0.0125), config.cfg (1), lam_cylinder.cfg (1.0)
Code: CConfig.cpp line 1406

PRANDTL_LAM

Laminar Prandtl number (0.72 (air), only for compressible flows)

More in config_template.cfg: Laminar Prandtl number (0.72 (air), only for CONSTANT_PRANDTL)

Type: list of real numbers
Default: 0.72
In config_template.cfg: PRANDTL_LAM= 0.72
Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics, Composition-Dependent model for Species Transport equations and 1 more
Used in 48 test case files, for example: air_nozzle_restart.cfg (0.72), fluid.cfg (6.96), disc_adj_heat.cfg (6.99091)
Code: CConfig.cpp line 1408

PRANDTL_TURB

Turbulent Prandtl number (0.9 (air), only for compressible flows) DEFAULT 0.90

More in config_template.cfg: Turbulent Prandtl number (0.9 (air) by default)

Type: list of real numbers
In config_template.cfg: PRANDTL_TURB= 0.90
Mentioned in: Setup Guide: Incompressible Flows, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics, Turbulence Models, Composition-Dependent model for Species Transport equations and 1 more
Used in 41 test case files, for example: air_nozzle_restart.cfg (0.90), datadriven_nozzle.cfg (0.8426621478074403), turb_SST_flatplate_compressibility_Sarkar.cfg (0.9)
Code: CConfig.cpp line 1410

WALLMODEL_KAPPA

von Karman constant used for the wall model DEFAULT 0.41

More in config_template.cfg: The von Karman constant, the constant below only affects the standard wall function model

Type: real number
Default: 0.41
In config_template.cfg: WALLMODEL_KAPPA= 0.41
Mentioned in: Markers and Boundary Conditions, 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 (0.41)
Code: CConfig.cpp line 1415

WALLMODEL_MAXITER

Max iterations used for the wall model DEFAULT 200

More in config_template.cfg: [Expert] Max Newton iterations used for the standard wall function

Type: integer
Default: 200
In config_template.cfg: WALLMODEL_MAXITER= 200
Mentioned in: Markers and Boundary Conditions, 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 (200)
Code: CConfig.cpp line 1417

WALLMODEL_RELFAC

Relaxation factor used for the wall model DEFAULT 0.5

More in config_template.cfg: [Expert] relaxation factor for the Newton iterations of the standard wall function

Type: real number
Default: 0.5
In config_template.cfg: WALLMODEL_RELFAC= 0.5
Mentioned in: Markers and Boundary Conditions, 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 (0.5)
Code: CConfig.cpp line 1419

WALLMODEL_MINYPLUS

lower limit for Y+ used for the wall model DEFAULT 5.0

More in config_template.cfg: The y+ value below which the wall function is switched off and we resolve the wall

Type: real number
Default: 5.0
In config_template.cfg: WALLMODEL_MINYPLUS= 5.0
Mentioned in: Markers and Boundary Conditions, Setup Guide: Steady RANS for External Aerodynamics, 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 (5.0)
Code: CConfig.cpp line 1421

WALLMODEL_B

constant B used for the wall model DEFAULT 5.5

More in config_template.cfg: The wall function model constant B

Type: real number
Default: 5.5
In config_template.cfg: WALLMODEL_B= 5.5
Mentioned in: Markers and Boundary Conditions, 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 (5.5)
Code: CConfig.cpp line 1423

BULK_MODULUS

Value of the Bulk Modulus DEFAULT 1.42E5

More in config_template.cfg: Bulk Modulus for computing the Mach number

Type: real number
Default: 1.42E5
In config_template.cfg: BULK_MODULUS= 1.42E5
Code: CConfig.cpp line 1426

BETA_FACTOR

Epsilon^2 multipier in Beta calculation for incompressible preconditioner.

Type: real number
Default: 4.1
In config_template.cfg: BETA_FACTOR= 4.1
Mentioned in: Setup Guide: Incompressible Flows
Used in 1 test case file, for example: solid.cfg (50)
Code: CConfig.cpp line 1428

MACH_NUMBER

Mach number (non-dimensional, based on the free-stream values). 0.0 by default

Type: real number
Default: 0.0
In config_template.cfg: MACH_NUMBER= 0.8
Mentioned in: Physical Definition, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Shape Optimization with the Discrete Adjoint, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Turbomachinery and 4 more
Used in 271 test case files, for example: aeroelastic_NACA64A010.cfg (0.85), air_nozzle_restart.cfg (1E-9), config.cfg (0.2)
Code: CConfig.cpp line 1430

INIT_OPTION

Init option to choose between Reynolds or thermodynamics quantities for initializing the solution

More in config_template.cfg: Init option to choose between Reynolds (default) or thermodynamics quantities for initializing the solution (REYNOLDS, TD_CONDITIONS)

Type: one of the values below
Values: REYNOLDS, TD_CONDITIONS
Default: REYNOLDS
In config_template.cfg: INIT_OPTION= REYNOLDS
Mentioned in: Physical Definition, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane, Non-ideal compressible flow in a supersonic nozzle and 1 more
Used in 69 test case files, for example: air_nozzle_restart.cfg (TD_CONDITIONS), flatPlate_rigidMotion_Conf.cfg (REYNOLDS)
Code: CConfig.cpp line 1432

INIT_OPTION_INC

Init option for the incompressible solver to choose between the initial density and the operating pressure for initializing the solution

More in config_template.cfg: Init option for the incompressible solver to choose between the initial density and the operating pressure for initializing the solution (DENSITY_INIT, OPERATING_PRESSURE). The default depends on the fluid model: DENSITY_INIT for INC_IDEAL_GAS and INC_IDEAL_GAS_POLY, OPERATING_PRESSURE for FLUID_MIXTURE and FLUID_FLAMELET. Not used by CONSTANT_DENSITY, nor by INC_DENSITY_MODEL= FLAMELET where the density is looked up in the flamelet manifold.

Type: one of the values below
Values: DENSITY_INIT, OPERATING_PRESSURE
Default: DENSITY_INIT
In config_template.cfg: % INIT_OPTION_INC= DENSITY_INIT
Mentioned in: Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion
Used in 1 test case file, for example: species2_primitiveVenturi_operatingpressure.cfg (OPERATING_PRESSURE)
Code: CConfig.cpp line 1436

FREESTREAM_OPTION

Free-stream option to choose between density and temperature for initializing the solution

More in config_template.cfg: Free-stream option to choose between density and temperature (default) for initializing the solution (TEMPERATURE_FS, DENSITY_FS)

Type: one of the values below
Values: TEMPERATURE_FS, DENSITY_FS
Default: TEMPERATURE_FS
In config_template.cfg: FREESTREAM_OPTION= TEMPERATURE_FS
Mentioned in: Physical Definition, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Turbomachinery, Aachen turbine stage with Mixing-plane, Non-ideal compressible flow in a supersonic nozzle and 1 more
Used in 69 test case files, for example: air_nozzle_restart.cfg (TEMPERATURE_FS), configFlow.cfg (DENSITY_FS)
Code: CConfig.cpp line 1438

FREESTREAM_PRESSURE

Free-stream pressure (101325.0 N/m^2 by default)

More in config_template.cfg: Free-stream pressure (101325.0 N/m^2, 2116.216 psf by default)

Type: real number
Default: 101325.0
In config_template.cfg: FREESTREAM_PRESSURE= 101325.0
Mentioned in: Physical Definition, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Shape Optimization with the Discrete Adjoint, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Turbomachinery, Setup Guide: Unsteady Flows and DES and 3 more
Used in 172 test case files, for example: aeroelastic_NACA64A010.cfg (101325.0), air_nozzle_restart.cfg (1400000), inv_wedge_ROE.cfg (100000.0)
Code: CConfig.cpp line 1440

FREESTREAM_DENSITY

Free-stream density (1.2886 Kg/m^3 (air), 998.2 Kg/m^3 (water)) DEFAULT -1.0 (calculated from others)

More in config_template.cfg: Free-stream density (1.2886 Kg/m^3, 0.0025 slug/ft^3 by default)

Type: real number
Default: -1.0
In config_template.cfg: FREESTREAM_DENSITY= 1.2886
Mentioned in: Physical Definition, Aachen turbine stage with Mixing-plane
Used in 37 test case files, for example: Arina2KRS.cfg (1.2092), circles.cfg (1.7418), configFlow.cfg (1.0)
Code: CConfig.cpp line 1442

FREESTREAM_TEMPERATURE

Free-stream temperature (288.15 K by default)

More in config_template.cfg: Free-stream temperature (288.15 K, 518.67 R by default)

Type: real number
Default: 288.15
In config_template.cfg: FREESTREAM_TEMPERATURE= 288.15
Mentioned in: Physical Definition, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Shape Optimization with the Discrete Adjoint, Setup Guide: Steady RANS for External Aerodynamics and 6 more
Used in 293 test case files, for example: aeroelastic_NACA64A010.cfg (288.15), air_nozzle_restart.cfg (373.15), config.cfg (270.0)
Code: CConfig.cpp line 1444

FREESTREAM_TEMPERATURE_VE

Free-stream vibrational-electronic temperature (288.15 K by default)

More in config_template.cfg: Free-stream VIBRATIONAL temperature (288.15 K, 518.67 R by default)

Type: real number
Default: 288.15
In config_template.cfg: FREESTREAM_TEMPERATURE_VE= 288.15
Mentioned in: Physical Definition
Used in 15 test case files, for example: invwedge_am.cfg (288.15), thermalbath.cfg (1000), cyl_ion_gy.cfg (246.87)
Code: CConfig.cpp line 1446

INC_DENSITY_MODEL

Option to choose the density model used in the incompressible flow solver.

More in config_template.cfg: Density model within the incompressible flow solver. Options are CONSTANT (default), BOUSSINESQ, VARIABLE, or FLAMELET. If VARIABLE, an appropriate fluid model must be selected. For FLAMELET, the density is retrieved directly from the flamelet manifold.

Type: one of the values below
Values: CONSTANT, BOUSSINESQ, VARIABLE, FLAMELET
Default: CONSTANT
In config_template.cfg: INC_DENSITY_MODEL= CONSTANT
Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Incompressible, Laminar Combustion Simulation, Incompressible, Laminar counterflow diffusion flame and 3 more
Used in 69 test case files, for example: flow_cylinder.cfg (VARIABLE), fluid.cfg (CONSTANT), lam_prem_ch4_cfd.cfg (FLAMELET)
Code: CConfig.cpp line 1452

INC_ENERGY_EQUATION

Solve the energy equation in the incompressible flow solver.

Type: YES / NO
Default: NO
In config_template.cfg: INC_ENERGY_EQUATION = NO
Mentioned in: History and Solution Output, Markers and Boundary Conditions, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Incompressible, Laminar Combustion Simulation and 6 more
Used in 69 test case files, for example: backwardStep.cfg (NO), flow_cylinder.cfg (YES)
Code: CConfig.cpp line 1454

TEMPERATURE_LIMITS

Temperature limits for incompressible flows (0.0, 5000 K by default)

More in config_template.cfg: Temperature limits for incompressible flows (0.0, 5000.0 K by default).

Type: fixed-size list of real numbers
Default: Not extracted; see the code.
In config_template.cfg: TEMPERATURE_LIMITS= 0.0, 5000.0
Mentioned in: Changes in Version 8, Setup Guide: Incompressible Flows
Used in 1 test case file, for example: active_species_transport_temp_limits.cfg (250, 400)
Code: CConfig.cpp line 1457

INC_DENSITY_REF

Reference density for incompressible flows

More in config_template.cfg: Reference density for incompressible flows (1.0 kg/m^3 by default)

Type: real number
Default: 1.0
In config_template.cfg: INC_DENSITY_REF= 1.0
Mentioned in: Physical Definition, Setup Guide: Incompressible Flows, Turbulent NACA 0012
Used in 9 test case files, for example: lam_bend.cfg (1.0)
Code: CConfig.cpp line 1459

INC_VELOCITY_REF

Reference velocity for incompressible flows (1.0 by default)

More in config_template.cfg: Reference velocity for incompressible flows (1.0 m/s by default)

Type: real number
Default: 1.0
In config_template.cfg: INC_VELOCITY_REF= 1.0
Mentioned in: Physical Definition, Setup Guide: Incompressible Flows, Turbulent NACA 0012
Used in 9 test case files, for example: lam_bend.cfg (1.0), pb_sphere.cfg (1)
Code: CConfig.cpp line 1461

INC_TEMPERATURE_REF

Reference temperature for incompressible flows with the energy equation (1.0 by default)

More in config_template.cfg: Reference temperature for incompressible flows that include the energy equation (1.0 K by default)

Type: real number
Default: 1.0
In config_template.cfg: INC_TEMPERATURE_REF = 1.0
Mentioned in: Physical Definition, Setup Guide: Incompressible Flows, Turbulent NACA 0012
Used in 6 test case files, for example: lam_bend.cfg (1.0)
Code: CConfig.cpp line 1463

INC_DENSITY_INIT

Initial density for incompressible flows (1.2886 kg/m^3 by default)

More in config_template.cfg: Initial density for incompressible flows (1.2886 kg/m^3 by default (air), 998.2 Kg/m^3 (water))

Type: real number
Default: 1.2886
In config_template.cfg: INC_DENSITY_INIT= 1.2886
Mentioned in: Physical Definition, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Inviscid Hydrofoil, Transitional Flat Plate and 2 more
Used in 83 test case files, for example: backwardStep.cfg (1.183), flow_cylinder.cfg (0.000210322), fluid.cfg (1.0e3)
Code: CConfig.cpp line 1465

INC_VELOCITY_INIT

Initial velocity for incompressible flows (1.0,0,0 m/s by default)

Type: fixed-size list of real numbers
Default: Not extracted; see the code.
In config_template.cfg: INC_VELOCITY_INIT= ( 1.0, 0.0, 0.0 )
Mentioned in: Physical Definition, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Inviscid Hydrofoil, Streamwise Periodic Flow and 4 more
Used in 84 test case files, for example: backwardStep.cfg (( 44.316, 0.0, 0.0 )), flow_cylinder.cfg (( 3.40297, 0.0, 0.0 )), fluid.cfg (( 2.0e-4, 0.0, 0.0 ))
Code: CConfig.cpp line 1468

INC_TEMPERATURE_INIT

Initial temperature for incompressible flows with the energy equation (288.15 K by default)

More in config_template.cfg: Initial temperature for incompressible flows that include the energy equation (288.15 K by default). Value is ignored if INC_ENERGY_EQUATION is false.

Type: real number
Default: 288.15
In config_template.cfg: INC_TEMPERATURE_INIT= 288.15
Mentioned in: Physical Definition, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Streamwise Periodicity, Laminar Flat Plate with Heat Transfer and 2 more
Used in 64 test case files, for example: backwardStep.cfg (298.333), flow_cylinder.cfg (288.15), def_intersect.cfg (300.0)
Code: CConfig.cpp line 1470

INC_NONDIM

Non-dimensionalization scheme for incompressible flows.

More in config_template.cfg: Non-dimensionalization scheme for incompressible flows. Options are INITIAL_VALUES (default), REFERENCE_VALUES, or DIMENSIONAL. INC_*_REF values are ignored unless REFERENCE_VALUES is chosen.

Type: one of the values below
Values: DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE, FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE, INITIAL_VALUES, REFERENCE_VALUES
Default: INITIAL_VALUES
In config_template.cfg: INC_NONDIM= INITIAL_VALUES
Mentioned in: Physical Definition, Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Species Transport and Combustion, Turbulent Bend with wall functions, Turbulent NACA 0012 and 1 more
Used in 88 test case files, for example: backwardStep.cfg (DIMENSIONAL), disc_adj_heat.cfg (INITIAL_VALUES)
Code: CConfig.cpp line 1472

INC_INLET_DAMPING

Damping factor applied to the iterative updates to the velocity at a pressure inlet in incompressible flow (0.1 by default).

More in config_template.cfg: Damping coefficient for iterative updates at pressure inlets. (0.1 by default)

Type: real number
Default: 0.1
In config_template.cfg: INC_INLET_DAMPING= 0.1
Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows
Used in 13 test case files, for example: def_intersect.cfg (0.1), lam_partial_prem_ch4_cfd.cfg (0.05), cylinder_split.cfg (0.01)
Code: CConfig.cpp line 1475

INC_OUTLET_DAMPING

Damping factor applied to the iterative updates to the pressure at a mass flow outlet in incompressible flow (0.1 by default).

More in config_template.cfg: Damping coefficient for iterative updates at mass flow outlets. (0.1 by default)

Type: real number
Default: 0.1
In config_template.cfg: INC_OUTLET_DAMPING= 0.1
Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows, Streamwise Periodic Flow
Used in 15 test case files, for example: def_intersect.cfg (0.1), lam_partial_prem_ch4_cfd.cfg (0.05), cylinder_split.cfg (0.01)
Code: CConfig.cpp line 1477

SPECIES_INIT

Initial values for scalar transport

Type: list of real numbers
In config_template.cfg: SPECIES_INIT= 1.0
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 30 test case files, for example: air_nozzle_species.cfg (0.25), lam_prem_ch4_cfd.cfg ((0.0, -210000, 0.0, 0.0)), lam_prem_ch4_hx_ad.cfg ((0, 0, 0, 0))
Code: CConfig.cpp line 1482

SPECIES_CLIPPING

Activate clipping for scalar transport equations

Type: YES / NO
Default: NO
In config_template.cfg: SPECIES_CLIPPING= NO
Mentioned in: Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Species Transport
Used in 30 test case files, for example: air_nozzle_species.cfg (YES), lam_prem_ch4_cfd.cfg (NO)
Code: CConfig.cpp line 1484

SPECIES_CLIPPING_MAX

Maximum values for scalar clipping

Type: list of real numbers
In config_template.cfg: SPECIES_CLIPPING_MAX= 1.0
Mentioned in: Setup Guide: Species Transport and Combustion, Species Transport
Used in 26 test case files, for example: air_nozzle_species.cfg (1.0), lam_prem_ch4_cfd.cfg (1 2e6 1 1), lam_partial_prem_ch4_cfd.cfg (0.3 2e6 1 1 1)
Code: CConfig.cpp line 1486

SPECIES_CLIPPING_MIN

Minimum values for scalar clipping

Type: list of real numbers
In config_template.cfg: SPECIES_CLIPPING_MIN= 0.0
Mentioned in: Setup Guide: Species Transport and Combustion, Species Transport
Used in 26 test case files, for example: air_nozzle_species.cfg (0.0), lam_prem_ch4_cfd.cfg (0 -2e6 0 0), lam_partial_prem_ch4_cfd.cfg (0 -3.0e6 0 0 0)
Code: CConfig.cpp line 1488

FLAME_INIT_METHOD

Ignition method for flamelet solver

More in config_template.cfg: Method used to ignite the solution: FLAME_FRONT : the flame is initialized using a plane, defined by a point and a normal. On one side, the solution is initialized using ‘burnt’ conditions and on the other side ‘unburnt’ conditions. The normal points in the direction of the ‘burnt’ condition. The ‘burnt’ condition is defined as the value of the progress variable for which the temperature exceeds the FLAME_INIT_IGNITION. SPARK : the solution is ignited through application of a set of source terms within a specified region for a set number of solver iterations. This artificial spark can be applied after a certain number of iterations has passed, allowing for the flow to evolve before igniting the mixture. NONE : no artificial solution ignition. By default, this option is set to NONE

Type: one of the values below
Values: NONE, FLAME_FRONT, SPARK
Default: NONE
In config_template.cfg: FLAME_INIT_METHOD= FLAME_FRONT
Mentioned in: Changes in Version 8, Setup Guide: Species Transport and Combustion, Incompressible, Laminar Combustion Simulation, Incompressible, Laminar counterflow diffusion flame
Used in 7 test case files, for example: lam_prem_ch4_cfd.cfg (NONE)
Code: CConfig.cpp line 1491

FLAME_ENTHALPY_BC

enthalpy BC for thermal walls. FLOW_MARKERS (default): enthalpy derived from MARKER_ISOTHERMAL temperature or MARKER_HEATFLUX via GetEnthFromTemp. SPECIES_MARKERS: enthalpy and all other scalars taken directly from MARKER_WALL_SPECIES or the Python wrapper (SetMarkerCustomScalar).

More in config_template.cfg: FLOW_MARKERS: flamelet method uses temperature BC from MARKER_INLET and MARKER_HEATFLUX/MARKER_ISOTHERMAL. It then does a reverse lookup for the enthalpy. SPECIES_MARKERS: flamelet method uses enthalpy from MARKER_INLET_SPECIES and MARKER_WALL_SPECIES.

Type: one of the values below
Values: FLOW_MARKERS, SPECIES_MARKERS
Default: FLOW_MARKERS
In config_template.cfg: FLAME_ENTHALPY_BC= SPECIES_MARKERS
Mentioned in: Flamelet Solver — Python Wrapper Wall Boundary Conditions, Setup Guide: Species Transport and Combustion, Incompressible, Laminar counterflow diffusion flame
Code: CConfig.cpp line 1495

FLAME_INIT

flame front initialization using the flamelet model

More in config_template.cfg: FLAME_FRONT initialization the flame is initialized using a plane, defined by a point and a normal. On one side, the solution is initialized using ‘burnt’ conditions and on the other side ‘unburnt’ conditions. The normal points in the direction of the ‘burnt’ condition. (x1,x2,x3) = point on the plane. (x4,x5,x6) = normal of the plane. (x7) = thickness of the reaction zone, this is the transition from unburnt to burnt conditions. (x8) = Thickness of the ‘burnt’ zone, after this length, the conditions will be ‘unburnt’ again.

Type: fixed-size list of real numbers
Default: Not extracted; see the code.
In config_template.cfg: FLAME_INIT= (0.004, 0.0, 0.0, 1.0, 0.0, 0.0, 0.2e-3, 1.0)
Mentioned in: Setup Guide: Species Transport and Combustion, Incompressible, Laminar Combustion Simulation, Incompressible, Laminar counterflow diffusion flame
Used in 8 test case files, for example: lam_prem_ch4_cfd.cfg ((0.0032, 0.00, 0.00, 1.0, 0.1, 0.0, 1.0e-3, 0.1)), lam_prem_ch4_hx_ad.cfg ((0.0035, 0, 0, 3.0, 2.0, 0.0, 5.0e-4, 1.0)), lam_prem_ch4_hx_dot.cfg ((0.0035, 0, 0, 3, 2, 0, 5.0e-4, 1.0))
Code: CConfig.cpp line 1497

SPARK_INIT

spark initialization using the flamelet model

More in config_template.cfg: SPARK initialization the solution is ignited through application of a set of source terms within a specified region for a set number of solver iterations. This artificial spark can be applied after a certain number of iterations has passed, allowing for the flow to evolve before igniting the mixture. (x1,x2,x3) = spark center location. (x4) = spark radius where within the artificial spark is applied. (x5,x6) = spark iteration start and number of iterations in which the artifical spark is applied. For single-zone problems the number of iterations are inner-loop iterations, for multi-zone problems, outer-loop iterations are considered.

Type: fixed-size list of real numbers
Default: Not extracted; see the code.
In config_template.cfg: SPARK_INIT= (0.004, 0.0, 0.0, 1e-4, 100, 10)
Mentioned in: Setup Guide: Species Transport and Combustion, Incompressible, Laminar Combustion Simulation
Used in 1 test case file, for example: laminar_premixed_h2_flame_cfd.cfg ((0.001, 0.0004, 0, 5e-4, 10, 10))
Code: CConfig.cpp line 1500

SPARK_REACTION_RATES

Net source term values applied to species within spark area during spark ignition.

More in config_template.cfg: Source terms (density times species time rate of change) applied to the species equations in the spark region for the duration of the spark. The number of terms should equate the total number of species in the flamelet problem.

Type: list of real numbers
In config_template.cfg: SPARK_REACTION_RATES= (1000, 0, 0)
Mentioned in: Setup Guide: Species Transport and Combustion, Incompressible, Laminar Combustion Simulation
Used in 1 test case file, for example: laminar_premixed_h2_flame_cfd.cfg ((1000, 0, 0))
Code: CConfig.cpp line 1503

THICKENED_FLAME_CORRECTION

Coarse grid correction for source terms and diffusive fluxes in reacting flows.

More in config_template.cfg: Thickened flame correction Approximate the thickness of the flame and suppress source terms and enhance diffusivity in cells with a lengthscale higher than the flame thickness.

Type: YES / NO
Default: YES
In config_template.cfg: THICKENED_FLAME_CORRECTION= YES
Mentioned in: Setup Guide: Species Transport and Combustion
Code: CConfig.cpp line 1506

FLAME_INIT_IGNITION

Ignition temperature for the flame initialization

More in config_template.cfg: Flame ignition temperature in Kelvin. Specify the temperature on the ‘burnt’ side of the flame when using FLAME_FRONT initialization or the maximum temperature within the spark region when using SPARK initialization. The initial value of the progress variable on the ‘burnt’ side of the flame front is calculated through inverse regression of the ignition temperature or when reaching the upper limit of the progress variable in the flamelet data space. The SPARK_REACTION_RATES are applied within the spark region when the local temperature is below the flame ignition temperature.

Type: real number
Default: 5000.0
In config_template.cfg: FLAME_INIT_IGNITION= 5000.0
Mentioned in: Setup Guide: Species Transport and Combustion
Code: CConfig.cpp line 1509

DIFFUSIVITY_MODEL

mass diffusivity model DEFAULT constant disffusivity

More in config_template.cfg: Mass diffusivity model (CONSTANT_DIFFUSIVITY, CONSTANT_SCHMIDT, UNITY_LEWIS, CONSTANT_LEWIS, FLAMELET)

Type: one of the values below
Values: CONSTANT_DIFFUSIVITY, CONSTANT_SCHMIDT, UNITY_LEWIS, CONSTANT_LEWIS, FLAMELET
Default: CONSTANT_DIFFUSIVITY
In config_template.cfg: DIFFUSIVITY_MODEL= CONSTANT_DIFFUSIVITY
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 30 test case files, for example: air_nozzle_species.cfg (CONSTANT_DIFFUSIVITY), lam_prem_ch4_cfd.cfg (FLAMELET), psi.cfg (CONSTANT_SCHMIDT)
Code: CConfig.cpp line 1514

DIFFUSIVITY_CONSTANT

mass diffusivity if DIFFUSIVITYMODEL::CONSTANT_DIFFUSIVITY is chosen DEFAULT 0.001 (Air)

More in config_template.cfg: Mass diffusivity if DIFFUSIVITY_MODEL= CONSTANT_DIFFUSIVITY is chosen. D_air ~= 0.001

Type: real number
Default: 0.001
In config_template.cfg: DIFFUSIVITY_CONSTANT= 0.001
Mentioned in: Setup Guide: Species Transport and Combustion, Species Transport
Used in 18 test case files, for example: air_nozzle_species.cfg (0.001), lam_prem_ch4_hx_ad.cfg (0.00001), psi.cfg (5.0e-5)
Code: CConfig.cpp line 1516

SCHMIDT_NUMBER_LAMINAR

Laminar Schmidt number of mass diffusion DEFAULT 1.0 (~for Gases)

More in config_template.cfg: Laminar Schmidt number for mass diffusion (for constant schmidt number model)

Type: real number
Default: 1.0
In config_template.cfg: SCHMIDT_NUMBER_LAMINAR= 1.0
Mentioned in: Setup Guide: Species Transport and Combustion
Used in 1 test case file, for example: psi.cfg (1.0)
Code: CConfig.cpp line 1518

SCHMIDT_NUMBER_TURBULENT

Turbulent Schmidt number of mass diffusion DEFAULT 0.70 (more or less experimental value)

Type: real number
Default: 0.7
In config_template.cfg: SCHMIDT_NUMBER_TURBULENT= 0.7
Mentioned in: Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Species Transport
Used in 2 test case files, for example: psi.cfg (0.7)
Code: CConfig.cpp line 1520

CONSTANT_LEWIS_NUMBER

: Constant Lewis number for mass diffusion

More in config_template.cfg: list of constant Lewis numbers for all species for

Type: list of real numbers
In config_template.cfg: CONSTANT_LEWIS_NUMBER= (1,1,1)
Mentioned in: Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations
Used in 2 test case files, for example: psi.cfg (1.0 1.0), species2_primitiveVenturi_mixingmodel_TURBULENT_MARKERS.cfg (0.365, 0.96)
Code: CConfig.cpp line 1522

FREESTREAM_VELOCITY

Free-stream velocity (m/s)

More in config_template.cfg: Free-stream velocity (1.0 m/s, 1.0 ft/s by default)

Type: fixed-size list of real numbers
Default: Not extracted; see the code.
In config_template.cfg: FREESTREAM_VELOCITY= ( 1.0, 0.00, 0.00 )
Mentioned in: Configuration File
Used in 8 test case files, for example: Arina2KRS.cfg (( 1.0, 0.00, 0.00 )), MFR_coupling.cfg (( 56.897550640000, 0.0, 0.0 )), cylinder_split.cfg (10.0 0.0 0.0)
Code: CConfig.cpp line 1526

FREESTREAM_VISCOSITY

Free-stream viscosity (1.853E-5 Ns/m^2 (air), 0.798E-3 Ns/m^2 (water))

More in config_template.cfg: Free-stream viscosity (1.853E-5 N s/m^2, 3.87E-7 lbf s/ft^2 by default)

Type: real number
Default: -1.0
In config_template.cfg: FREESTREAM_VISCOSITY= 1.853E-5
Mentioned in: Physical Definition
Used in 7 test case files, for example: MFR_coupling.cfg (1.78938027807758E-05), turb_ahmed.cfg (1.845E-5), unsteady_CHT_FlatPlate_Conf.cfg (1.82E-5)
Code: CConfig.cpp line 1528

FREESTREAM_INTERMITTENCY

Value for freestream intermittency (from config_template.cfg)

Type: real number
Default: 1.0
In config_template.cfg: FREESTREAM_INTERMITTENCY= 1.0
Mentioned in: Setup Guide: Laminar-Turbulent Transition, Transition Models
Used in 1 test case file, for example: trans_s809.cfg (0.9)
Code: CConfig.cpp line 1530

FREESTREAM_TURBULENCEINTENSITY

Free-stream turbulence intensity (from config_template.cfg)

Type: real number
Default: 0.05
In config_template.cfg: FREESTREAM_TURBULENCEINTENSITY= 0.05
Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Turbomachinery, Transition Models and 4 more
Used in 50 test case files, for example: circles.cfg (0.03), BC_HeatTransfer.cfg (0.05), ascii_output.cfg (0.00038729)
Code: CConfig.cpp line 1532

FREESTREAM_NU_FACTOR

No description in the code yet.

Type: real number
Default: 3.0
Not in config_template.cfg.
Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Steady RANS for External Aerodynamics, Transition Models, Turbulence Models
Used in 2 test case files, for example: dsma661_sa_config.cfg (3)
Code: CConfig.cpp line 1534

LOWER_LIMIT_K_FACTOR

Control lower limit constants of the SST model (Cphi_infinity) *(from config_template.cfg)

Type: real number
Default: 1.0e-15
In config_template.cfg: LOWER_LIMIT_K_FACTOR= 1e-15
Mentioned in: Changes in Version 8, Turbulence Models
Code: CConfig.cpp line 1536

LOWER_LIMIT_OMEGA_FACTOR

No description in the code yet.

Type: real number
Default: 1e-05
In config_template.cfg: LOWER_LIMIT_OMEGA_FACTOR= 1e-5
Mentioned in: Changes in Version 8, Turbulence Models
Code: CConfig.cpp line 1538

ENGINE_NU_FACTOR

Engine nu factor (SA model). (from config_template.cfg)

Type: real number
Default: 3.0
In config_template.cfg: ENGINE_NU_FACTOR= 3.0
Mentioned in: Turbulence Models
Used in 3 test case files, for example: actuatordisk_bem.cfg (0.0), propeller.cfg (30.0)
Code: CConfig.cpp line 1540

ACTDISK_SECONDARY_FLOW

secondary flow value for actuator disk (from config_template.cfg)

Type: real number
Default: 0.0
In config_template.cfg: ACTDISK_SECONDARY_FLOW= 0.0
Code: CConfig.cpp line 1542

INITIAL_BCTHRUST

Initial BC Thrust guess for POWER or D-T driver (4000.0 lbf by default) (from config_template.cfg)

Type: real number
Default: 4000.0
In config_template.cfg: INITIAL_BCTHRUST= 4000.0
Code: CConfig.cpp line 1544

FREESTREAM_TURB2LAMVISCRATIO

Free-stream ratio between turbulent and laminar viscosity (from config_template.cfg)

Type: real number
Default: 10.0
In config_template.cfg: FREESTREAM_TURB2LAMVISCRATIO= 10.0
Mentioned in: Markers and Boundary Conditions, Setup Guide: Incompressible Flows, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Turbomachinery, Transition Models and 2 more
Used in 45 test case files, for example: circles.cfg (100.0), BC_HeatTransfer.cfg (10.0), ascii_output.cfg (0.009)
Code: CConfig.cpp line 1546

SIDESLIP_ANGLE

Side-slip angle (degrees, only for compressible flows)

Type: real number
Default: 0.0
In config_template.cfg: SIDESLIP_ANGLE= 0.0
Mentioned in: Physical Definition, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Unsteady Flows and DES, Inviscid ONERA M6, Turbulent ONERA M6
Used in 79 test case files, for example: inv_ONERAM6.cfg (0.0)
Code: CConfig.cpp line 1548

AOA

Angle of attack (degrees, only for compressible flows)

Type: real number
Default: 0.0
In config_template.cfg: AOA= 1.25
Mentioned in: Physical Definition, 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, Actuator Disk With Variable Load and 7 more
Used in 226 test case files, for example: aeroelastic_NACA64A010.cfg (1.0), config.cfg (0.0), inv_NACA0012.cfg (1.25)
Code: CConfig.cpp line 1550

FIXED_CL_MODE

Activate fixed CL mode (specify a CL instead of AoA).

More in config_template.cfg: Activate fixed lift mode (specify a CL instead of AoA, NO/YES)

Type: YES / NO
Default: NO
In config_template.cfg: FIXED_CL_MODE= NO
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, Setup Guide: Steady RANS for External Aerodynamics, Constrained shape design of a transonic inviscid wing at a cte. C_L, Constrained shape design of a transonic turbulent airfoil at a cte. C_L, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA
Used in 3 test case files, for example: inv_ONERAM6.cfg (NO), inv_NACA0012.cfg (YES)
Code: CConfig.cpp line 1552

EVAL_DOF_DCX

Evaluate the dOF_dCL or dOF_dCMy during run time.

Type: YES / NO
Default: NO
In config_template.cfg: EVAL_DOF_DCX= NO
Mentioned in: Constrained shape design of a transonic turbulent airfoil at a cte. C_L
Used in 2 test case files, for example: inv_NACA0012.cfg (YES)
Code: CConfig.cpp line 1554

DISCARD_INFILES

DIscard the angle of attack in the solution and the increment in the geometry files.

More in config_template.cfg: Discard the data storaged in the solution and geometry files e.g. AOA, dCL/dAoA, dCD/dCL, iter, etc. Note that AoA in the solution and geometry files is critical to aero design using AoA as a variable. (NO, YES)

Type: YES / NO
Default: NO
In config_template.cfg: DISCARD_INFILES= NO
Used in 10 test case files, for example: Arina2KRS.cfg (NO), inv_ONERAM6.cfg (YES)
Code: CConfig.cpp line 1556

TARGET_CL

Specify a fixed coefficient of lift instead of AoA (only for compressible flows)

More in config_template.cfg: Target coefficient of lift for fixed lift mode (0.80 by default)

Type: real number
Default: 0.0
In config_template.cfg: TARGET_CL= 0.80
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, Setup Guide: Steady RANS for External Aerodynamics, Constrained shape design of a transonic inviscid wing at a cte. C_L, Constrained shape design of a transonic turbulent airfoil at a cte. C_L, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA
Used in 3 test case files, for example: inv_ONERAM6.cfg (0.286), inv_NACA0012.cfg (0.30)
Code: CConfig.cpp line 1558

DCL_DALPHA

Damping factor for fixed CL mode.

More in config_template.cfg: Estimation of dCL/dAlpha (0.2 per degree by default)

Type: real number
Default: 0.2
In config_template.cfg: DCL_DALPHA= 0.2
Mentioned in: Setup Guide: Steady RANS for External Aerodynamics, Constrained shape design of a transonic inviscid wing at a cte. C_L, Constrained shape design of a transonic turbulent airfoil at a cte. C_L, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA
Used in 3 test case files, for example: inv_ONERAM6.cfg (0.1), inv_NACA0012.cfg (0.2)
Code: CConfig.cpp line 1560

UPDATE_AOA_ITER_LIMIT

Maximum number of iterations between AoA updates for fixed CL problem.

Type: integer
Default: 200
In config_template.cfg: UPDATE_AOA_ITER_LIMIT= 100
Mentioned in: Setup Guide: Steady RANS for External Aerodynamics, Constrained shape design of a transonic inviscid wing at a cte. C_L, Constrained shape design of a transonic turbulent airfoil at a cte. C_L, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA
Used in 3 test case files, for example: inv_ONERAM6.cfg (100), inv_NACA0012.cfg (20)
Code: CConfig.cpp line 1562

UPDATE_IH

Number of times Alpha is updated in a fix CL problem.

Type: integer
Default: 5
In config_template.cfg: UPDATE_IH= 5
Code: CConfig.cpp line 1564

ITER_DCL_DALPHA

Number of iterations to evaluate dCL_dAlpha .

More in config_template.cfg: Number of iterations to evaluate dCL_dAlpha by using finite differences (500 by default)

Type: integer
Default: 500
In config_template.cfg: ITER_DCL_DALPHA= 500
Mentioned in: Setup Guide: Steady RANS for External Aerodynamics, Constrained shape design of a transonic inviscid wing at a cte. C_L, Constrained shape design of a transonic turbulent airfoil at a cte. C_L, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA
Used in 3 test case files, for example: inv_ONERAM6.cfg (500), inv_NACA0012.cfg (50), inv_NACA0012_ContAdj.cfg (250)
Code: CConfig.cpp line 1566

DNETTHRUST_DBCTHRUST

Value of dNetThrust/dBCThrust

More in config_template.cfg: Estimate of dNetThrust/dBCThrust used in the actuator-disk thrust update.

Type: real number
Default: 1.0
In config_template.cfg: DNETTHRUST_DBCTHRUST= 1.0
Code: CConfig.cpp line 1568

UPDATE_BCTHRUST

Number of times Alpha is updated in a fix CL problem.

More in config_template.cfg: Number of times BC Thrust is updated in a fix Net Thrust problem (5 by default)

Type: integer
Default: 5
In config_template.cfg: UPDATE_BCTHRUST= 100
Code: CConfig.cpp line 1570

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