Spatial Discretization

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.

NUM_METHOD_GRAD

Numerical method for spatial gradients

More in config_template.cfg: Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)

Type: one of the values below
Values: NONE, GREEN_GAUSS, LEAST_SQUARES, WEIGHTED_LEAST_SQUARES
Default: WEIGHTED_LEAST_SQUARES
In config_template.cfg: NUM_METHOD_GRAD= GREEN_GAUSS
Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Shape Optimization with the Discrete Adjoint, Setup Guide: Species Transport and Combustion and 4 more
Used in 340 test case files, for example: aeroelastic_NACA64A010.cfg (GREEN_GAUSS), inv_ONERAM6.cfg (WEIGHTED_LEAST_SQUARES)
Code: CConfig.cpp line 2135

NUM_METHOD_GRAD_RECON

Numerical method for spatial gradients used only for upwind reconstruction

More in config_template.cfg: Numerical method for spatial gradients to be used for MUSCL reconstruction Options are (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES, LEAST_SQUARES). Default value is NONE and the method specified in NUM_METHOD_GRAD is used.

Type: one of the values below
Values: NONE, GREEN_GAUSS, LEAST_SQUARES, WEIGHTED_LEAST_SQUARES
Default: NONE
In config_template.cfg: NUM_METHOD_GRAD_RECON = LEAST_SQUARES
Mentioned in: Setup Guide: Steady RANS for External Aerodynamics
Used in 11 test case files, for example: turb_NACA0012_sa.cfg (LEAST_SQUARES), MFR_coupling.cfg (GREEN_GAUSS)
Code: CConfig.cpp line 2138

VENKAT_LIMITER_COEFF

Coefficient for the limiter. DEFAULT value 0.05. Larger values decrease the extent of limiting, values approaching zero cause lower-order approximation to the solution.

More in config_template.cfg: Coefficient for Venkatakrishnan-type limiters (upwind scheme). A larger value decreases the extent of limiting, values approaching zero cause lower-order approximation to the solution (0.05 by default)

Type: real number
Default: 0.05
In config_template.cfg: VENKAT_LIMITER_COEFF= 0.05
Mentioned in: Setup Guide: Laminar-Turbulent Transition, Setup Guide: Steady RANS for External Aerodynamics, Slope Limiters and Shock Resolution, Troubleshooting, Laminar Cylinder
Used in 163 test case files, for example: config.cfg (0.03), inv_wedge_ROE.cfg (0.006), lam_NACA0012.cfg (1.0)
Code: CConfig.cpp line 2141

ADJ_SHARP_LIMITER_COEFF

Coefficient for detecting the limit of the sharp edges. DEFAULT value 3.0. Use with sharp edges limiter.

More in config_template.cfg: Coefficient for the adjoint sharp edges limiter (3.0 by default).

Type: real number
Default: 3.0
In config_template.cfg: ADJ_SHARP_LIMITER_COEFF= 3.0
Mentioned in: Slope Limiters and Shock Resolution
Used in 59 test case files, for example: inv_NACA0012.cfg (3.0), inv_ONERAM6_basic.cfg (1.0)
Code: CConfig.cpp line 2144

LIMITER_ITER

Freeze the value of the limiter after a number of iterations. DEFAULT value 999999.
Type: integer
Default: 999999
In config_template.cfg: LIMITER_ITER= 999999
Mentioned in: Setup Guide: Laminar-Turbulent Transition, Setup Guide: Shape Optimization with the Discrete Adjoint, Setup Guide: Steady RANS for External Aerodynamics, Slope Limiters and Shock Resolution, Troubleshooting
Used in 47 test case files, for example: def_cylindrical.cfg (999999), def_NACA4412.cfg (99999)
Code: CConfig.cpp line 2147

CONV_NUM_METHOD_FLOW

Convective numerical method

More in config_template.cfg: Convective numerical method (JST, JST_KE, JST_MAT, LAX-FRIEDRICH, ROE, AUSM, AUSMPLUSUP, AUSMPLUSUP2, AUSMPLUSM, HLLC, TURKEL_PREC, SW, MSW, FDS, SLAU, SLAU2, L2ROE, LMROE, LD2)

Type: special format, see config_template.cfg
Values: See Upwind_Map , Centered_Map.
In config_template.cfg: CONV_NUM_METHOD_FLOW= ROE
Mentioned in: Changes in Version 8, Convective Schemes, Hybrid RANS/LES (DES), Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Laminar-Turbulent Transition and 8 more
Used in 321 test case files, for example: aeroelastic_NACA64A010.cfg (JST), air_nozzle_restart.cfg (ROE), backwardStep.cfg (LD2)
Code: CConfig.cpp line 2151

NUM_METHOD_FEM_FLOW

Numerical method

More in config_template.cfg: FEM numerical method (DG)

Type: special format, see config_template.cfg
Values: See FEM_Map , Centered_Map.
In config_template.cfg: NUM_METHOD_FEM_FLOW= DG
Used in 35 test case files, for example: InviscidVortex.cfg (DG)
Code: CConfig.cpp line 2155

MUSCL_FLOW

Check if the MUSCL scheme should be used

More in config_template.cfg: Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations. Required for 2nd order upwind schemes (NO, YES)

Type: YES / NO
Default: YES
In config_template.cfg: MUSCL_FLOW= YES
Mentioned in: Changes in Version 8, Convective Schemes, Hybrid RANS/LES (DES), Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Laminar-Turbulent Transition and 9 more
Used in 231 test case files, for example: air_nozzle_restart.cfg (YES), backwardStep.cfg (NO)
Code: CConfig.cpp line 2158

MUSCL_KAPPA_FLOW

Blending coefficient for the U-MUSCL scheme

More in config_template.cfg: Coefficient for blending upwind and central differences in MUSCL scheme. Values range from -1 (fully one-sided) to 1 (central difference).

Type: real number
Default: 0.0
In config_template.cfg: MUSCL_KAPPA_FLOW= 0.0
Mentioned in: Changes in Version 8, Setup Guide: Steady RANS for External Aerodynamics
Used in 5 test case files, for example: turb_NACA0012_sa.cfg (0.5)
Code: CConfig.cpp line 2160

RAMP_MUSCL

Enable ramping of the MUSCL scheme from 1st to 2nd order using specified method

More in config_template.cfg: Option to ramp the MUSCL reconstruction scheme gradually from first to second order

Type: YES / NO
Default: NO
In config_template.cfg: RAMP_MUSCL= NO
Mentioned in: Changes in Version 8, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Turbomachinery, Troubleshooting
Used in 1 test case file, for example: Axial_stage2D.cfg (YES)
Code: CConfig.cpp line 2162

RAMP_MUSCL_COEFF

brief RAMP_MUSCL_COEFF the 1st coeff is the ramp start iteration, the 2nd coeff is the iteration update frequenct, 3rd coeff is the total number of iterations

More in config_template.cfg: Coefficients for the MUSCL ramp, 1st is ramp start iteration, 2nd is the ramp update frequency, 3rd is the total number of iterations of the ramp

Type: fixed-size list of integers
Default: Not extracted; see the code.
In config_template.cfg: RAMP_MUSCL_COEFF= (1000.0, 10.0, 500.0)
Mentioned in: Setup Guide: Turbomachinery, Troubleshooting
Used in 1 test case file, for example: Axial_stage2D.cfg ((0.0, 1.0, 20.0))
Code: CConfig.cpp line 2166

RAMP_MUSCL_POWER

DESRCIPTION: Exponent of the MUSCL ramp formulation

More in config_template.cfg: Value for modifying how aggresively the ramp is applied (cannot be less than or equal to 0) < 1 = Aggresive ramp up early, slower later, > 1 slow initial ramping, more aggresive towards end

Type: real number
Default: 1.0
In config_template.cfg: RAMP_MUSCL_POWER = 1
Used in 1 test case file, for example: Axial_stage2D.cfg (1)
Code: CConfig.cpp line 2168

KIND_MUSCL_RAMP

The kind of MUSCL Ramp to be applied

Type: one of the values below
Values: ITERATION, SMOOTH_FUNCTION
Default: ITERATION
In config_template.cfg: KIND_MUSCL_RAMP= ITERATION
Mentioned in: Changes in Version 8
Code: CConfig.cpp line 2170

SLOPE_LIMITER_FLOW

DESCRIPTION: Slope limiter for the direct solution.

More in config_template.cfg: Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG, BARTH_JESPERSEN, VAN_ALBADA_EDGE, NISHIKAWA_R3, NISHIKAWA_R4, NISHIKAWA_R5)

Type: one of the values below
Values: NONE, VENKATAKRISHNAN, NISHIKAWA_R3, NISHIKAWA_R4, NISHIKAWA_R5, VENKATAKRISHNAN_WANG, BARTH_JESPERSEN, VAN_ALBADA_EDGE, SHARP_EDGES, WALL_DISTANCE
Default: VENKATAKRISHNAN
In config_template.cfg: SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer, Setup Guide: Incompressible Flows, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics and 6 more
Used in 224 test case files, for example: air_nozzle_restart.cfg (NONE), config.cfg (VENKATAKRISHNAN), circles.cfg (VAN_ALBADA_EDGE)
Code: CConfig.cpp line 2173

JST_SENSOR_COEFF

2nd and 4th order artificial dissipation coefficients for the JST method

More in config_template.cfg: 2nd and 4th order artificial dissipation coefficients for the JST method ( 0.5, 0.02 by default )

Type: fixed-size list of real numbers
Default: Not extracted; see the code.
In config_template.cfg: JST_SENSOR_COEFF= ( 0.5, 0.02 )
Mentioned in: Convective Schemes, 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, Laminar Cylinder
Used in 187 test case files, for example: aeroelastic_NACA64A010.cfg (( 0.5, 0.02 )), backwardStep.cfg (( 0.0, 0.002 )), lam_cylinder.cfg (( 0.0, 0.001 ))
Code: CConfig.cpp line 2176

LAX_SENSOR_COEFF

1st order artificial dissipation coefficients for the Lax-Friedrichs method.

More in config_template.cfg: 1st order artificial dissipation coefficients for the Lax–Friedrichs method ( 0.15 by default )

Type: real number
Default: 0.15
In config_template.cfg: LAX_SENSOR_COEFF= 0.15
Mentioned in: Convective Schemes, Laminar Cylinder
Used in 6 test case files, for example: Arina2KRS.cfg (0.15), species2_primitiveVenturi_Lax_Friedrich.cfg (0.01)
Code: CConfig.cpp line 2178

USE_ACCURATE_FLUX_JACOBIANS

Use numerically computed Jacobians for AUSM+up(2) and SLAU(2)

More in config_template.cfg: Use numerically computed Jacobians for AUSM+up(2) and SLAU(2) Slower per iteration but potentialy more stable and capable of higher CFL

Type: YES / NO
Default: NO
In config_template.cfg: USE_ACCURATE_FLUX_JACOBIANS= NO
Mentioned in: Convective Schemes
Code: CConfig.cpp line 2180

CENTRAL_JACOBIAN_FIX_FACTOR

Improve the numerical properties (diagonal dominance) of the global Jacobian matrix, 3 to 4 is “optimum” (central schemes)

More in config_template.cfg: Higher values than 1 (3 to 4) make the global Jacobian of central schemes (compressible flow only) more diagonal dominant (but mathematically incorrect) so that higher CFL can be used.

Type: real number
Default: 4.0
In config_template.cfg: CENTRAL_JACOBIAN_FIX_FACTOR= 4.0
Mentioned in: Convective Schemes
Code: CConfig.cpp line 2182

CENTRAL_INC_JACOBIAN_FIX_FACTOR

Control numerical properties of the global Jacobian matrix using a multiplication factor for incompressible central schemes

Type: real number
Default: 1.0
In config_template.cfg: CENTRAL_INC_JACOBIAN_FIX_FACTOR= 1.0
Code: CConfig.cpp line 2184

CONV_NUM_METHOD_ADJFLOW

Convective numerical method for the adjoint solver.

More in config_template.cfg: Convective numerical method (JST, LAX-FRIEDRICH, ROE)

Type: special format, see config_template.cfg
Values: See Upwind_Map , Centered_Map. Note: not all methods are guaranteed to be implemented for the adjoint solver.
In config_template.cfg: CONV_NUM_METHOD_ADJFLOW= JST
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA
Used in 61 test case files, for example: inv_NACA0012.cfg (ROE), inv_ONERAM6.cfg (JST), def_intersect.cfg (FDS)
Code: CConfig.cpp line 2189

MUSCL_ADJFLOW

Check if the MUSCL scheme should be used

Type: YES / NO
Default: YES
In config_template.cfg: MUSCL_ADJFLOW= YES
Mentioned in: Changes in Version 8, Slope Limiters and Shock Resolution
Used in 16 test case files, for example: inv_NACA0012.cfg (YES), transonic_stator.cfg (NO)
Code: CConfig.cpp line 2191

MUSCL_KAPPA_ADJFLOW

Blending coefficient for the U-MUSCL scheme

Type: real number
Default: 0.0
In config_template.cfg: MUSCL_KAPPA_ADJFLOW= 0.0
Code: CConfig.cpp line 2193

SLOPE_LIMITER_ADJFLOW

DESCRIPTION: Slope limiter for the adjoint solution.
Type: one of the values below
Values: NONE, VENKATAKRISHNAN, NISHIKAWA_R3, NISHIKAWA_R4, NISHIKAWA_R5, VENKATAKRISHNAN_WANG, BARTH_JESPERSEN, VAN_ALBADA_EDGE, SHARP_EDGES, WALL_DISTANCE
Default: VENKATAKRISHNAN
In config_template.cfg: SLOPE_LIMITER_ADJFLOW= VENKATAKRISHNAN
Mentioned in: Slope Limiters and Shock Resolution, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA
Used in 27 test case files, for example: inv_NACA0012.cfg (NONE), turb_ONERAM6.cfg (VENKATAKRISHNAN), rotating_NACA0012.cfg (SHARP_EDGES)
Code: CConfig.cpp line 2196

ADJ_JST_SENSOR_COEFF

2nd and 4th order artificial dissipation coefficients for the adjoint JST method.

More in config_template.cfg: 2nd, and 4th order artificial dissipation coefficients for the adjoint JST method ( 0.5, 0.02 by default )

Type: fixed-size list of real numbers
Default: Not extracted; see the code.
In config_template.cfg: ADJ_JST_SENSOR_COEFF= ( 0.5, 0.02 )
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA
Used in 59 test case files, for example: inv_NACA0012.cfg (( 0.5, 0.02 )), inv_ONERAM6.cfg (( 0.0, 0.02 )), lam_cylinder.cfg (( 0.0, 0.001 ))
Code: CConfig.cpp line 2199

ADJ_LAX_SENSOR_COEFF

1st order artificial dissipation coefficients for the adjoint Lax-Friedrichs method.

More in config_template.cfg: 1st order artificial dissipation coefficients for the adjoint Lax–Friedrichs method ( 0.15 by default )

Type: real number
Default: 0.15
In config_template.cfg: ADJ_LAX_SENSOR_COEFF= 0.15
Used in 1 test case file, for example: heated_cylinder.cfg (0.15)
Code: CConfig.cpp line 2201

MUSCL_TURB

Check if the MUSCL scheme should be used

Type: YES / NO
Default: NO
In config_template.cfg: MUSCL_TURB= NO
Mentioned in: Setup Guide: Laminar-Turbulent Transition, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics, Setup Guide: Turbomachinery, Setup Guide: Unsteady Flows and DES and 3 more
Used in 133 test case files, for example: backwardStep.cfg (NO), turb_NACA0012_sa.cfg (YES)
Code: CConfig.cpp line 2204

MUSCL_KAPPA_TURB

Blending coefficient for the U-MUSCL scheme

Type: real number
Default: 0.0
In config_template.cfg: MUSCL_KAPPA_TURB= 0.0
Mentioned in: Changes in Version 8
Used in 5 test case files, for example: turb_NACA0012_sa.cfg (0.0)
Code: CConfig.cpp line 2206

SLOPE_LIMITER_TURB

Slope limiter
Type: one of the values below
Values: NONE, VENKATAKRISHNAN, NISHIKAWA_R3, NISHIKAWA_R4, NISHIKAWA_R5, VENKATAKRISHNAN_WANG, BARTH_JESPERSEN, VAN_ALBADA_EDGE, SHARP_EDGES, WALL_DISTANCE
Default: VENKATAKRISHNAN
In config_template.cfg: SLOPE_LIMITER_TURB= VENKATAKRISHNAN
Mentioned in: Setup Guide: Laminar-Turbulent Transition, Slope Limiters and Shock Resolution, Turbulent Flat Plate
Used in 92 test case files, for example: turb_nasa.cfg (VENKATAKRISHNAN), turb_NACA0012_sa.cfg (NONE)
Code: CConfig.cpp line 2209

CONV_NUM_METHOD_TURB

Convective numerical method

More in config_template.cfg: Convective numerical method (SCALAR_UPWIND, BOUNDED_SCALAR)

Type: special format, see config_template.cfg
In config_template.cfg: CONV_NUM_METHOD_TURB= SCALAR_UPWIND
Mentioned in: Convective Schemes, Setup Guide: Incompressible Flows, Setup Guide: Laminar-Turbulent Transition, Setup Guide: Non-Ideal Compressible Flows, Setup Guide: Species Transport and Combustion, Setup Guide: Steady RANS for External Aerodynamics and 4 more
Used in 144 test case files, for example: air_nozzle_restart.cfg (SCALAR_UPWIND), psi.cfg (BOUNDED_SCALAR)
Code: CConfig.cpp line 2212

USE_ACCURATE_TURB_JACOBIANS

Use numerically computed Jacobians for Standard SA model

More in config_template.cfg: Use numerically computed exact Jacobians for turbulence models Slower per iteration but potentialy more stable and capable of higher CFL

Type: YES / NO
Default: NO
In config_template.cfg: USE_ACCURATE_TURB_JACOBIANS= NO
Mentioned in: Changes in Version 8
Code: CConfig.cpp line 2214

MUSCL_ADJTURB

Check if the MUSCL scheme should be used

Type: YES / NO
Default: NO
In config_template.cfg: MUSCL_ADJTURB= NO
Mentioned in: Slope Limiters and Shock Resolution
Used in 1 test case file, for example: transonic_stator.cfg (NO)
Code: CConfig.cpp line 2217

SLOPE_LIMITER_ADJTURB

Slope limiter
Type: one of the values below
Values: NONE, VENKATAKRISHNAN, NISHIKAWA_R3, NISHIKAWA_R4, NISHIKAWA_R5, VENKATAKRISHNAN_WANG, BARTH_JESPERSEN, VAN_ALBADA_EDGE, SHARP_EDGES, WALL_DISTANCE
Default: VENKATAKRISHNAN
In config_template.cfg: SLOPE_LIMITER_ADJTURB= VENKATAKRISHNAN
Mentioned in: Slope Limiters and Shock Resolution
Code: CConfig.cpp line 2220

CONV_NUM_METHOD_ADJTURB

Convective numerical method for the adjoint/turbulent problem

More in config_template.cfg: Convective numerical method (SCALAR_UPWIND)

Type: special format, see config_template.cfg
In config_template.cfg: CONV_NUM_METHOD_ADJTURB= SCALAR_UPWIND
Used in 1 test case file, for example: transonic_stator.cfg (SCALAR_UPWIND)
Code: CConfig.cpp line 2222

MUSCL_SPECIES

Check if the MUSCL scheme should be used DEFAULT false

More in config_template.cfg: Monotonic Upwind Scheme for Conservation Laws (TVD) in the species equations. Required for 2nd order upwind schemes (NO, YES)

Type: YES / NO
Default: NO
In config_template.cfg: MUSCL_SPECIES= NO
Mentioned in: Setup Guide: Species Transport and Combustion, Slope Limiters and Shock Resolution, Composition-Dependent model for Species Transport equations, Species Transport
Used in 29 test case files, for example: lam_prem_ch4_cfd.cfg (YES), lam_prem_ch4_hx_ad.cfg (NO)
Code: CConfig.cpp line 2225

MUSCL_KAPPA_SPECIES

Blending coefficient for the U-MUSCL scheme

More in config_template.cfg: Same as MUSCL_KAPPA_FLOW but for species transport.

Type: real number
Default: 0.0
In config_template.cfg: MUSCL_KAPPA_SPECIES= 0.0
Code: CConfig.cpp line 2227

SLOPE_LIMITER_SPECIES

Slope limiter

More in config_template.cfg: Slope limiter for species equations (same as SLOPE_LIMITER_TURB)

Type: one of the values below
Values: NONE, VENKATAKRISHNAN, NISHIKAWA_R3, NISHIKAWA_R4, NISHIKAWA_R5, VENKATAKRISHNAN_WANG, BARTH_JESPERSEN, VAN_ALBADA_EDGE, SHARP_EDGES, WALL_DISTANCE
Default: NONE
In config_template.cfg: SLOPE_LIMITER_SPECIES = NONE
Mentioned in: Setup Guide: Species Transport and Combustion, Slope Limiters and Shock Resolution, Composition-Dependent model for Species Transport equations, Species Transport
Used in 29 test case files, for example: lam_prem_ch4_cfd.cfg (NONE)
Code: CConfig.cpp line 2229

CONV_NUM_METHOD_SPECIES

Convective numerical method for species transport

More in config_template.cfg: Convective numerical method for species transport (SCALAR_UPWIND, BOUNDED_SCALAR)

Type: special format, see config_template.cfg
In config_template.cfg: CONV_NUM_METHOD_SPECIES= SCALAR_UPWIND
Mentioned in: Setup Guide: Species Transport and Combustion, Composition-Dependent model for Species Transport equations, Incompressible, Laminar Combustion Simulation, Species Transport
Used in 29 test case files, for example: lam_prem_ch4_cfd.cfg (BOUNDED_SCALAR), turb_SA_flatplate_species.cfg (SCALAR_UPWIND)
Code: CConfig.cpp line 2231

MUSCL_HEAT

Check if the MUSCL scheme should be used

Type: YES / NO
Default: NO
In config_template.cfg: MUSCL_HEAT= YES
Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer
Used in 2 test case files, for example: disc_adj_heat.cfg (YES)
Code: CConfig.cpp line 2234

MUSCL_KAPPA_HEAT

Blending coefficient for the U-MUSCL scheme

More in config_template.cfg: Same as MUSCL_KAPPA_FLOW but for the heat equation.

Type: real number
Default: 0.0
In config_template.cfg: MUSCL_KAPPA_HEAT= 0.0
Code: CConfig.cpp line 2236

SLOPE_LIMITER_HEAT

Slope limiter

More in config_template.cfg: Slope limiter for the heat equation (same options as SLOPE_LIMITER_SPECIES)

Type: one of the values below
Values: NONE, VENKATAKRISHNAN, NISHIKAWA_R3, NISHIKAWA_R4, NISHIKAWA_R5, VENKATAKRISHNAN_WANG, BARTH_JESPERSEN, VAN_ALBADA_EDGE, SHARP_EDGES, WALL_DISTANCE
Default: NONE
In config_template.cfg: SLOPE_LIMITER_HEAT = NONE
Code: CConfig.cpp line 2238

CONV_NUM_METHOD_HEAT

Convective numerical method

More in config_template.cfg: Convective numerical method for the heat equation (only SCALAR_UPWIND)

Type: special format, see config_template.cfg
In config_template.cfg: CONV_NUM_METHOD_HEAT= SCALAR_UPWIND
Mentioned in: Setup Guide: Heat Transfer and Conjugate Heat Transfer
Used in 2 test case files, for example: disc_adj_heat.cfg (SCALAR_UPWIND)
Code: CConfig.cpp line 2240

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