NACA Regression Tests

Let's test some of the ProjectX solvers for the case of a NACA0012 (? check ?) airfoil (2D) in compressible, inciscid flow:

  • 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 >

what this solver tests
result

what this solver tests
result

what this solver tests
result

what this solver tests
result