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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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title	Inputs:

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Common flow parameters:
- Freestream Mach number: M _∞ = 0.5
- Angle of attack: α = 0 °
- Total pressure: P_t =
- Total temperature: T_t =
- Static temperature:
- CFL: 10³⁰

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width	50%

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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