NACA Regression Tests
Let's test some of the ProjectX solvers for the case of a NACA0012 (? check ?) airfoil (2D) in compressible, inciscid flow:
Parameters:
- Freestream Mach number: M ∞ = 0.5
- Angle of attack: α = 0 °
- Total pressure: Pt; =
- Total temperature: Tt; =
- Static temperature:
< insert grid image here > < insert primal solution here >
Newton-Jacobi (Right)
what this solver tests
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Newton-Jacobi
what this solver tests
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Newton-ILU
what this solver tests
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Newton-ILUT
what this solver tests
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