Note: This is the tutorial used in Get started.
The following is an aerodynamic shape optimization case for the NACA0012 airfoil at low speed.
Case: Airfoil aerodynamic optimization Geometry: NACA0012 Objective function: Drag coefficient (CD) Lift coefficient (CL): 0.5 Design variables: 20 free-form deformation (FFD) points moving in the y direction, one angle of attack Constraints: Symmetry, volume, thickness, and lift constraints (total number: 34) Mach number: 0.02941 (10 m/s) Reynolds number: 0.6667 million Mesh cells: ~4,000 Solver: DASimpleFoam
Fig. 1. Mesh and FFD points for the NACA0012 airfoil
The evoluation of pressure and shape during the optimization is as follows. Refer to this page for post-processing the optimization results.
Fig. 2. Pressure and shape evolution during the optimization process