Problem:
Lift and Drag calculation for a rectangular wing (0.5 m span x 0.15 m chord x uniform cross section of NACA 9410), at horizontal velocity of 10 km/h.
A very simple CFD problem (with 177250 cells) solved on a 4 core Haswell-DT, varying the number of CPU cores used each time; CPU times are as below:
Cores used CPU time taken for solution (1 travel convergence)
1/4 core 782 seconds (2.31x slower)
2/4 cores 468 seconds (1.38x slower)
3/4 cores 380 seconds (1.12x slower)
4/4 cores 339 seconds (1x)
Lift and Drag calculation for a rectangular wing (0.5 m span x 0.15 m chord x uniform cross section of NACA 9410), at horizontal velocity of 10 km/h.
A very simple CFD problem (with 177250 cells) solved on a 4 core Haswell-DT, varying the number of CPU cores used each time; CPU times are as below:
Cores used CPU time taken for solution (1 travel convergence)
1/4 core 782 seconds (2.31x slower)
2/4 cores 468 seconds (1.38x slower)
3/4 cores 380 seconds (1.12x slower)
4/4 cores 339 seconds (1x)
