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 correctly.
In some cases, the solvers are also run in parallel using MPI and compared with the solvers run in serial.
section
Column
width
50%
Panel
title
Inputs:
Common flow parameters:
Freestream Mach number: M ∞ = 0.5
Angle of attack: α = 0 °
Total pressure: Pt =
Total temperature: Tt =
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
Section
Column
width
50%
Panel
title
Boundary conditions:
Column
width
50%
Panel
title
Input Primal X-Momentum
...
Section
Column
width
50%
Panel
title
Newton-Jacobi (Left):
Nonlinear solver:
Newton
Preconditioner:
Block Jacobi (left)
Serial results:
Residual norm converges to 4.3571·10^-13^ after 5 iterations
Drag coefficient: CD = .5318 counts
Lift coefficient: CL = .9638 counts
Column
width
50%
Panel
title
Newton-Jacobi (Right):
Nonlinear solver:
Newton
Preconditioner:
Block Jacobi (right)
Results:
Residual norm converges to 4.3532·10^-13^ after 5 iterations
