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Let's test some of the ProjectX solvers for the case of a NACA0012 (? check ?) airfoil (2D) in compressible, inciscid flow:
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- Common flow parameters:
- Freestream Mach number: M ∞ = 0.5
- Angle of attack: α = 0 °
- Total pressure: Pt =
- Total temperature: Tt =
- Static temperature:
- CFL: 1030
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- Common solver parameters:
- Preconditioning:
- Outer GMRES iterations (no. restarts): 20
- Inner GMRES iterations (no. Krylov vectors): 200
- Solution order: 2
- PSequencing: False
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| title | Boundary conditions: |
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| title | Input Primal X-Momentum |
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Tests on linear solvers:
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