The following is an aerodynamic shape optimization case for the DPW4 aircraft (wing-body-tail configuration) at transonic conditions.
Case: Aircraft aerodynamic optimization Geometry: CRM wing, body, and tail Objective function: Drag coefficient Design variables: 216 FFD points moving in the z direction, 9 wing twists, one tail rotation, one angle of attack Constraints: Volume, thickness, LE/TE, and lift constraints (total number: 771) Mach number: 0.85 Reynolds number: 5 million Mesh cells: 860 K Solver: DARhoSimpleCFoam
Fig. 1. Mesh and FFD points for the DPW4 wing-body-tail configuration
To run this case, first download tutorials and untar it. Then go to tutorials-master/DPW4_Aircraft and run the “preProcessing.sh” script to generate the mesh:
We recommend running this case on an HPC system with 100 CPU cores:
mpirun -np 100 python runScript.py 2>&1 | tee logOpt.txt