Header
CHECK KEYWORDS Warn
Mesh DB "." "."
Include Path ""
Results Directory "Results/"
End
Simulation
Max Output Level = 5
Coordinate System = Cartesian
Coordinate Mapping(3) = 1 2 3
Simulation Type = Transient
Steady State Max Iterations = 1
Output Intervals(1) = 1
Timestep intervals(1) = $1/0.05
Timestep Sizes(1) = 0.05
Timestepping Method = BDF
BDF Order = 2
Solver Input File = case.sif
Post File = Fields/case.dat
Binary Output = False
End
Constants
Gravity(4) = 0 -1 0 9.82
Stefan Boltzmann = 5.670374419e-08
Permittivity of Vacuum = 8.85418781e-12
Permeability of Vacuum = 1.25663706e-6
Boltzmann Constant = 1.380649e-23
Unit Charge = 1.6021766e-19
End
Body 1
Target Bodies(1) = 1
Name = "Body 1"
Equation = 1
Material = 1
End
Solver 1
Equation = SaveScalars
Procedure = "SaveData" "SaveScalars"
Variable 1 = Flow Solution Loads 1
Parallel Reduce = True
Operator 1 = boundary sum
File Append = True
Variable 2 = Flow Solution Loads 2
Filename = fluidForces.dat
Exec Solver = Always
End
Solver 2
Equation = Navier-Stokes
Calculate Loads = True
Procedure = "FlowSolve" "FlowSolver"
Variable = Flow Solution[Velocity:2 Pressure:1]
Exec Solver = Always
Stabilize = True
Optimize Bandwidth = True
Steady State Convergence Tolerance = 1.0e-5
Nonlinear System Convergence Tolerance = 1.0e-4
Nonlinear System Max Iterations = 10
Nonlinear System Newton After Iterations = 3
Nonlinear System Newton After Tolerance = 1.0e-3
Nonlinear System Relaxation Factor = 0.5
Linear System Solver = Iterative
Linear System Iterative Method = BiCGStab
Linear System Max Iterations = 1000000
Linear System Convergence Tolerance = 1.0e-6
BiCGstabl polynomial degree = 2
Linear System Preconditioning = ILU0
Linear System ILUT Tolerance = 1.0e-3
Linear System Abort Not Converged = False
Linear System Residual Output = 10
Linear System Precondition Recompute = 1
End
Equation 1
Name = "NSEqs"
Active Solvers(2) = 1 2
End
Material 1
Name = "Air"
Density = 1
Viscosity = $1/50
End
Boundary Condition 1
Target Boundaries(1) = 1
Name = "Inlet"
Velocity 2 = 0
Velocity 1 = 1
End
Boundary Condition 2
Target Boundaries(2) = 6 7
Name = "Outlet"
Velocity 2 = 0
End
Boundary Condition 3
Target Boundaries(1) = 8
Name = "Airfoil"
Noslip wall BC = True
Save Scalars = True
End
Boundary Condition 4
Target Boundaries(4) = 2 3 4 5
Name = "Walls"
Noslip wall BC = True
End