Results
The developed code was run on a cluster of dual Pentium III processors
Computations were performed for
- Inviscid subsonic flow over NACA 0012 airfoil (single grid solution)
- Inviscid transonic flow over RAE 2822 airfoil (single and multigrid solutions)
- Inviscid transonic flow over root section of Onera M6 wing (single and multigrid solutions)