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NS_Predictor_airfoil.i
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NS_Predictor_airfoil.i
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[Mesh]
second_order = true
[fmg]
type = FileMeshGenerator
file = Mesh3.exo
[]
[]
#[Mesh]
# file = NACA_airfoil_Pred.e
#[]
[Variables]
# x-star velocity
[./u_star]
order = SECOND
family = LAGRANGE
#initial_from_file_var = u_star
#initial_from_file_timestep = LATEST
[./InitialCondition]
type = ConstantIC
value = 1.0
[../]
[../]
# y-star velocity
[./v_star]
order = SECOND
family = LAGRANGE
#initial_from_file_var = v_star
#initial_from_file_timestep = LATEST
[./InitialCondition]
type = ConstantIC
value = 0.05
[../]
[../]
[]
[AuxVariables]
# x-velocity
[./u]
order = SECOND
family = L2_LAGRANGE
#initial_from_file_var = u
#initial_from_file_timestep = LATEST
[./InitialCondition]
type = ConstantIC
value = 1.0
[../]
[../]
# y-velocity
[./v]
order = SECOND
family = L2_LAGRANGE
#initial_from_file_var = v
#initial_from_file_timestep = LATEST
[./InitialCondition]
type = ConstantIC
value = 0.0
[../]
[../]
[./u_old]
order = SECOND
family = L2_LAGRANGE
#initial_from_file_var = u
#initial_from_file_timestep = LATEST
[../]
# Pressure
[./p]
order = FIRST
family = LAGRANGE
#initial_from_file_var = p
#initial_from_file_timestep = LATEST
[./InitialCondition]
type = ConstantIC
value = 0
[../]
[../]
[./p_old]
order = FIRST
family = LAGRANGE
#initial_from_file_var = p
#initial_from_file_timestep = LATEST
[../]
[]
[Kernels]
[./x_predictor]
type = NavStokesPredictor_p
variable = u_star
u = u
v = v
u_star = u_star
v_star = v_star
p = p
component = 0
[../]
[./y_predictor]
type = NavStokesPredictor_p
variable = v_star
u = u
v = v
u_star = u_star
v_star = v_star
p = p
component = 1
[../]
[]
[AuxKernels]
[./normalization_auxkernel]
type = NormalizationAux
variable = u_old
source_variable = u
normal_factor = 1.0
execute_on = timestep_end
# Note: 'normalization' or 'shift' are provided as CLI args
[../]
[./normalization_auxkernel2]
type = NormalizationAux
variable = p_old
source_variable = p
normal_factor = 1.0
execute_on = timestep_end
# Note: 'normalization' or 'shift' are provided as CLI args
[../]
[]
[BCs]
[./x_no_slip]
type = DirichletBC
variable = u_star
boundary = 'WALL AIRFOIL'
value = 0.0
[../]
[./y_no_slip]
type = DirichletBC
variable = v_star
boundary = 'WALL AIRFOIL'
value = 0.0
[../]
[./velocity_inlet_x]
type = DirichletBC
variable = u_star
boundary = 'INLET'
value = 1.0
[]
[./velocity_inlet_y]
type = DirichletBC
variable = v_star
boundary = 'INLET'
value = 0.0
[]
[]
[Materials]
[./const]
type = GenericConstantMaterial
#block = 'FLUID'
block = 'SOLID'
prop_names = 'rho mu'
prop_values = '1 0.002'
[../]
[]
[Preconditioning]
[./SMP]
type = SMP
full = true
#solve_type = 'NEWTON'
solve_type = 'LINEAR'
[../]
[]
[Executioner]
type = Transient
#num_steps = 10
#dt = .06
#dtmin =
#petsc_options_iname = '-pc_type'
#petsc_options_value = 'lu'
#petsc_options_iname = '-ksp_gmres_restart -pc_type -sub_pc_type -sub_pc_factor_levels'
#petsc_options_value = '300 bjacobi ilu 4'
petsc_options_iname = '-ksp_type -pc_type -sub_pc_type -snes_max_it -sub_pc_factor_shift_type -pc_asm_overlap -snes_atol -snes_rtol '
petsc_options_value = 'gmres asm lu 100 NONZERO 2 1E-14 1E-12'
#petsc_options_iname = '-ksp_type -pc_type -pc_sub_type -sub_pc_factor_levels'
#petsc_options_value = 'gmres asm ilu 4'
#petsc_options_iname = '-pc_type -pc_asm_overlap -sub_pc_type -sub_pc_factor_levels' #Option 2
#petsc_options_value = 'asm 2 ilu 4'
#line_search = 'none'
nl_rel_tol = 1e-8
nl_abs_tol = 1e-9
nl_max_its = 40
l_tol = 1e-8
l_max_its = 500
[]
#[Outputs]
# file_base = NACA_airfoil_Pred
# exodus = true
# checkpoint = true
#[]