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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
- 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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{center}
{panel:title=Boundary conditions:}
!nacabcs.png|border=1,scale=.6,width=388,height=292!
{panel}
{center}
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Tests on linear solvers:
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| title | Newton-Jacobi (Left): |
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| - Nonlinear solver:
- Preconditioner:
- Serial results:
- Residual norm converges to 4.3571·10^-13^ after 5 iterations
- Drag coefficient: CD = .5318 counts
- Lift coefficient: CL = .9638 counts
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| title | Newton-Jacobi (Right): |
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| - Nonlinear solver:
- Preconditioner:
- Results:
- Residual norm converges to 4.3532·10^-13^ after 5 iterations
- Drag coefficient: CD = .5318 counts
- Lift coefficient: CL = .9638 counts
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