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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:

Panel
titleParameters:
  • Freestream Mach number: M ∞ = 0.5
  • Angle of attack: α = 0 °
  • Total pressure: Pt; =
  • Total temperature: Tt; =
  • Static temperature:
  • M-\infty-
  • dfd

< insert grid image here > < insert primal solution here >

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