Python Options

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.

GRADIENT_METHOD

Gradient method

Type: used by the Python scripts only
Not in config_template.cfg.
Code: CConfig.cpp line 3035

GEO_PARAM

Geometrical Parameter

Type: used by the Python scripts only
Not in config_template.cfg.
Code: CConfig.cpp line 3038

DEFINITION_DV

Setup for design variables

More in config_template.cfg: Optimization design variables, separated by semicolons

Type: used by the Python scripts only
In config_template.cfg: DEFINITION_DV= ( 1, 1.0 | airfoil | 0, 0.05 ); ( 1, 1.0 | airfoil | 0, 0.10 ); ( 1, 1.0 | airfoil | 0, 0.15 ); ( 1, 1.0 | airfoil | 0, 0.20 ); ( 1, 1.0 | airfoil | 0, 0.25 ); ( 1, 1.0 | airfoil | 0, 0.30 ); ( 1, 1.0 | airfoil | 0, 0.35 ); ( 1, 1.0 | airfoil | 0, 0.40 ); ( 1, 1.0 | airfoil | 0, 0.45 ); ( 1, 1.0 | airfoil | 0, 0.50 ); ( 1, 1.0 | airfoil | 0, 0.55 ); ( 1, 1.0 | airfoil | 0, 0.60 ); ( 1, 1.0 | airfoil | 0, 0.65 ); ( 1, 1.0 | airfoil | 0, 0.70 ); ( 1, 1.0 | airfoil | 0, 0.75 ); ( 1, 1.0 | airfoil | 0, 0.80 ); ( 1, 1.0 | airfoil | 0, 0.85 ); ( 1, 1.0 | airfoil | 0, 0.90 ); ( 1, 1.0 | airfoil | 0, 0.95 ); ( 1, 1.0 | airfoil | 1, 0.05 ); ( 1, 1.0 | airfoil | 1, 0.10 ); ( 1, 1.0 | airfoil | 1, 0.15 ); ( 1, 1.0 | airfoil | 1, 0.20 ); ( 1, 1.0 | airfoil | 1, 0.25 ); ( 1, 1.0 | airfoil | 1, 0.30 ); ( 1, 1.0 | airfoil | 1, 0.35 ); ( 1, 1.0 | airfoil | 1, 0.40 ); ( 1, 1.0 | airfoil | 1, 0.45 ); ( 1, 1.0 | airfoil | 1, 0.50 ); ( 1, 1.0 | airfoil | 1, 0.55 ); ( 1, 1.0 | airfoil | 1, 0.60 ); ( 1, 1.0 | airfoil | 1, 0.65 ); ( 1, 1.0 | airfoil | 1, 0.70 ); ( 1, 1.0 | airfoil | 1, 0.75 ); ( 1, 1.0 | airfoil | 1, 0.80 ); ( 1, 1.0 | airfoil | 1, 0.85 ); ( 1, 1.0 | airfoil | 1, 0.90 ); ( 1, 1.0 | airfoil | 1, 0.95 )
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, 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, Shape Design With Multiple Objectives and Penalty Functions, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA, Unconstrained shape design of a two way mixing channel
Used in 72 test case files, for example: inv_NACA0012.cfg (( 30, 1.0 | airfoil | 0, 0.05 ); ( 30, 1.0 | airfoil | 0, 0.10 ); ( 30, 1.0 | airfoil | 0, 0.15 ); ( 30, 1.0 | airfoil | 0, 0.20 ); ( 30, 1.0 | airfoil | 0, 0.25 ); ( 30, 1.0 | airfoil | 0, 0.30 ); ( 30, 1.0 | airfoil | 0, 0.35 ); ( 30, 1.0 | airfoil | 0, 0.40 ); ( 30, 1.0 | airfoil | 0, 0.45 ); ( 30, 1.0 | airfoil | 0, 0.50 ); ( 30, 1.0 | airfoil | 0, 0.55 ); ( 30, 1.0 | airfoil | 0, 0.60 ); ( 30, 1.0 | airfoil | 0, 0.65 ); ( 30, 1.0 | airfoil | 0, 0.70 ); ( 30, 1.0 | airfoil | 0, 0.75 ); ( 30, 1.0 | airfoil | 0, 0.80 ); ( 30, 1.0 | airfoil | 0, 0.85 ); ( 30, 1.0 | airfoil | 0, 0.90 ); ( 30, 1.0 | airfoil | 0, 0.95 ); ( 30, 1.0 | airfoil | 1, 0.05 ); ( 30, 1.0 | airfoil | 1, 0.10 ); ( 30, 1.0 | airfoil | 1, 0.15 ); ( 30, 1.0 | airfoil | 1, 0.20 ); ( 30, 1.0 | airfoil | 1, 0.25 ); ( 30, 1.0 | airfoil | 1, 0.30 ); ( 30, 1.0 | airfoil | 1, 0.35 ); ( 30, 1.0 | airfoil | 1, 0.40 ); ( 30, 1.0 | airfoil | 1, 0.45 ); ( 30, 1.0 | airfoil | 1, 0.50 ); ( 30, 1.0 | airfoil | 1, 0.55 ); ( 30, 1.0 | airfoil | 1, 0.60 ); ( 30, 1.0 | airfoil | 1, 0.65 ); ( 30, 1.0 | airfoil | 1, 0.70 ); ( 30, 1.0 | airfoil | 1, 0.75 ); ( 30, 1.0 | airfoil | 1, 0.80 ); ( 30, 1.0 | airfoil | 1, 0.85 ); ( 30, 1.0 | airfoil | 1, 0.90 ); ( 30, 1.0 | airfoil | 1, 0.95 )), inv_NACA0012_FD.cfg (( 30, 1.0 | airfoil | 0, 0.05 ); ( 30, 1.0 | airfoil | 0, 0.10 ); ( 30, 1.0 | airfoil | 0, 0.15 );), inv_ONERAM6.cfg (( 11, 1.0 | WING | MAIN_BOX, 0, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 8, 1, 0.0, 0.0, 1.0 ))
Code: CConfig.cpp line 3041

OPT_ITERATIONS

Maximum number of iterations

Type: used by the Python scripts only
In config_template.cfg: OPT_ITERATIONS= 100
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, 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, Shape Design With Multiple Objectives and Penalty Functions, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA
Used in 25 test case files, for example: inv_ONERAM6.cfg (100), inv_wedge_ROE_multiobj.cfg (1), def_intersect.cfg (20)
Code: CConfig.cpp line 3044

OPT_ACCURACY

Requested accuracy

Type: used by the Python scripts only
In config_template.cfg: OPT_ACCURACY= 1E-10
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, 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, Shape Design With Multiple Objectives and Penalty Functions, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA
Used in 24 test case files, for example: inv_ONERAM6.cfg (1E-6), def_intersect.cfg (1E-200), Arina2KRS.cfg (1E-1)
Code: CConfig.cpp line 3047

OPT_COMBINE_OBJECTIVE

Flag specifying whether to internally combine a multi-objective function or treat separately

More in config_template.cfg: Use combined objective within gradient evaluation: may reduce cost to compute gradients when using the adjoint formulation.

Type: used by the Python scripts only
In config_template.cfg: OPT_COMBINE_OBJECTIVE = NO
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, Shape Design With Multiple Objectives and Penalty Functions
Used in 6 test case files, for example: inv_wedge_ROE_multiobj.cfg (YES), inv_wedge_ROE_2surf_1obj.cfg (NO)
Code: CConfig.cpp line 3051

DV_VALUE_NEW

Current value of the design variables

Type: used by the Python scripts only
Not in config_template.cfg.
Code: CConfig.cpp line 3054

DV_VALUE_OLD

Previous value of the design variables

Type: used by the Python scripts only
Not in config_template.cfg.
Code: CConfig.cpp line 3057

NUMBER_PART

Number of partitions of the mesh

Type: used by the Python scripts only
Not in config_template.cfg.
Code: CConfig.cpp line 3060

OPT_OBJECTIVE

Optimization objective function with optional scaling factor

More in config_template.cfg: Optimization objective function with scaling factor, separated by semicolons. To include quadratic penalty function: use OPT_CONSTRAINT option syntax within the OPT_OBJECTIVE list. ex= Objective * Scale

Type: used by the Python scripts only
In config_template.cfg: OPT_OBJECTIVE= DRAG
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, 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, Shape Design With Multiple Objectives and Penalty Functions, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA, Unsteady Shape Optimization NACA0012
Used in 66 test case files, for example: inv_NACA0012.cfg (DRAG * 0.001), inv_ONERAM6.cfg (DRAG * 1.0), inv_wedge_ROE.cfg (SURFACE_TOTAL_PRESSURE)
Code: CConfig.cpp line 3063

OPT_CONSTRAINT

Optimization constraint functions with optional scaling factor

More in config_template.cfg: Optimization constraint functions with pushing factors (affects its value, not the gradient in the python scripts), separated by semicolons ex= (Objective = Value ) * Scale, use ‘>’,’<’,’=’

Type: used by the Python scripts only
In config_template.cfg: OPT_CONSTRAINT= ( LIFT > 0.328188 ) * 0.001; ( MOMENT_Z > 0.034068 ) * 0.001; ( AIRFOIL_THICKNESS > 0.11 ) * 0.001
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, 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, Shape Design With Multiple Objectives and Penalty Functions, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA, Unsteady Shape Optimization NACA0012
Used in 55 test case files, for example: inv_NACA0012.cfg (( LIFT > 0.327 ) * 0.001; ( MOMENT_Z > 0.0 ) * 0.001; ( AIRFOIL_THICKNESS > 0.12 ) * 0.001), inv_ONERAM6.cfg (( LIFT > 0.282557 ) * 1.0), inv_wedge_ROE.cfg (NONE)
Code: CConfig.cpp line 3066

FIN_DIFF_STEP

Finite different step for gradient estimation

More in config_template.cfg: Finite difference step size for python scripts (0.001 default, recommended 0.001 x REF_LENGTH)

Type: used by the Python scripts only
In config_template.cfg: FIN_DIFF_STEP = 0.001
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint
Used in 6 test case files, for example: inv_NACA0012_FD.cfg (0.001), def_intersect.cfg (1e-3), FD_configMaster.cfg (1e-8)
Code: CConfig.cpp line 3069

CONSOLE

Verbosity of the python scripts to Stdout

Type: used by the Python scripts only
Not in config_template.cfg.
Code: CConfig.cpp line 3072

DECOMPOSED

Flag specifying if the mesh was decomposed

Type: used by the Python scripts only
Not in config_template.cfg.
Code: CConfig.cpp line 3075

OPT_GRADIENT_FACTOR

Optimization gradient factor

More in config_template.cfg: Factor to reduce the norm of the gradient (affects the objective function and gradient in the python scripts) In general, a norm of the gradient ~1E-6 is desired.

Type: used by the Python scripts only
In config_template.cfg: OPT_GRADIENT_FACTOR= 1E-6
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, 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 6 test case files, for example: def_intersect.cfg (1.0), Arina2KRS.cfg (1E-6), naca0012.cfg (0.1)
Code: CConfig.cpp line 3078

OPT_BOUND_UPPER

Upper bound for the optimizer

More in config_template.cfg: Upper bound for each design variable (bound in the python optimizer)

Type: used by the Python scripts only
In config_template.cfg: OPT_BOUND_UPPER= 1E10
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, 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, Shape Design With Multiple Objectives and Penalty Functions, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA, Unsteady Shape Optimization NACA0012
Used in 24 test case files, for example: inv_ONERAM6.cfg (0.1), def_intersect.cfg (1e10), Arina2KRS.cfg (5E-3)
Code: CConfig.cpp line 3081

OPT_BOUND_LOWER

Lower bound for the optimizer

More in config_template.cfg: Lower bound for each design variable (bound in the python optimizer)

Type: used by the Python scripts only
In config_template.cfg: OPT_BOUND_LOWER= -1E10
Mentioned in: Setup Guide: Shape Optimization with the Discrete Adjoint, 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, Shape Design With Multiple Objectives and Penalty Functions, Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA, Unsteady Shape Optimization NACA0012
Used in 24 test case files, for example: inv_ONERAM6.cfg (-0.1), def_intersect.cfg (-1e10), Arina2KRS.cfg (-5E-3)
Code: CConfig.cpp line 3084

NZONES

Number of zones of the problem

Type: used by the Python scripts only
Not in config_template.cfg.
Used in 11 test case files, for example: inv_NACA0012.cfg (1), FD_configMaster.cfg (2), multi_interface_rst.cfg (3)
Code: CConfig.cpp line 3087

PARMETIS_TOLERANCE

ParMETIS load balancing tolerance

More in config_template.cfg: Load balancing tolerance, lower values will make ParMETIS work harder to evenly distribute the work-estimate metric across all MPI ranks, at the expense of more edge cuts (i.e. increased communication cost).

Type: real number
Default: 0.02
In config_template.cfg: PARMETIS_TOLERANCE= 0.02
Used in 3 test case files, for example: config.cfg (0.05)
Code: CConfig.cpp line 3090

PARMETIS_POINT_WEIGHT

ParMETIS load balancing weight for points

Type: integer
Default: 0
In config_template.cfg: PARMETIS_POINT_WEIGHT= 0
Used in 3 test case files, for example: config.cfg (1)
Code: CConfig.cpp line 3093

PARMETIS_EDGE_WEIGHT

ParMETIS load balancing weight for edges (equiv. to neighbors)

More in config_template.cfg: The work-estimate metric is a weighted function of the work-per-edge (e.g. spatial discretization, linear system solution) and of the work-per-point (e.g. source terms, temporal discretization) the former usually accounts for >90% of the total. These weights are INTEGERS (for compatibility with ParMETIS) thus not [0, 1]. To balance memory usage (instead of computation) the point weight needs to be increased (especially for explicit time integration methods).

Type: integer
Default: 1
In config_template.cfg: PARMETIS_EDGE_WEIGHT= 1
Used in 3 test case files, for example: config.cfg (0)
Code: CConfig.cpp line 3096

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