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Let's test some of the ProjectX solvers for the case of a NACA0012 airfoil in compressible, inviscid flow.

Each test case starts with an initial primal solution (sample x-momentum shown below). After reading the input, ProjectX runs a particular test case. Subsequently, all numerical data stored in the history (.hist) files are compared with a "true" history file.

In some cases, the solvers are also run in parallel using MPI and compared with the solvers run in serial. The drag and lift coefficients along with residual convergence are given.

For more information, please consult the .job and .hist files located in the corner of each panel.

• Common flow parameters:
  • Equation set: Compressible 2D Euler
  • Freestream Mach number: M _∞ = 0.5
  • Angle of attack: α = 0 °
  • Total pressure: P_t =
  • Total temperature: T_t =
  • 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

• Almost all parameters are identical to the previous adaptation test. The only differing parameters are:
  • Target degree-of-freedom increase factor: 1.25
  • Curved re-meshing type: Elasticity
• Serial results:
  • Initial mesh:
    • DOF = 990
    • Error estimate = 3.9138·10^-4
    • Drag = 5.3180·10^-4
  • First adaptation:
    • DOF = 1008
    • Error estimate = 1.8590·10^-4
    • Drag = 2.6109·10^-4
  • Second adaptation:
    • DOF = 1278
    • Error estimate = 8.5377·10^-5
    • Drag = 1.3336·10^-4

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