Examples

The examples/ directory contains two complete cases. Both read their mesh from the repository’s meshes/ directory, build the model as described in the user guide, and by default compare the adjoint derivatives with finite differences (sim.check_totals). To optimize instead, uncomment the modOpt block at the end of the script.

Run them from any directory, for example

$ OMP_NUM_THREADS=1 mpirun -n 4 python examples/airfoil_opt.py

airfoil_opt.py: 2D airfoil

Mesh	naca0012_euler_mesh_quad_v2: quadrilaterals around a NACA 0012 airfoil
Flow	\(M_\infty = 0.8\), \(\alpha = 2^\circ\)
Design variables	vertical motion of 5 x 3 FFD control points (bounds \(\pm 0.01\)); \(\alpha \in [1.75^\circ, 2.25^\circ]\)
Objective, constraint	minimize drag \(D\) subject to lift \(L \ge 0.225\)
Optional (commented out)	camber and thickness variables; area and thickness constraints

wing_opt.py: 3D wing

Mesh	wing_vol_L3_xdmf: hexahedra around the Simple Transonic Wing (half-wing, symmetry plane at \(y = 0\)); wing_vol_L3_xdmf_wallmerged is the same mesh with merged wall layers (fewer cells, lower aspect ratio)
Flow	\(M_\infty = 0.8\), \(\alpha = 2^\circ\)
Design variables	vertical motion of 3 x 5 x 2 control points of a swept, tapered FFD block (bounds \(\pm 0.1\)); \(\alpha \in [1.5^\circ, 2.5^\circ]\)
Objective, constraint	minimize drag \(D\) subject to lift \(L \ge 10\)
Optional (commented out)	twist and chord variables; volume, thickness and planform-area constraints