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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, the results for various nonlinear solvers and linear preconditioners are then compared with previously obtained data to ensure the solvers function correctlyProjectX runs on a particular test case. Subsequently, all numerical output stored in the history (.hist) files is 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