NSNoPenetrationBC

under construction:Undocumented Class

The NSNoPenetrationBC has not been documented. The content listed below should be used as a starting point for documenting the class, which includes the typical automatic documentation associated with a MooseObject; however, what is contained is ultimately determined by what is necessary to make the documentation clear for users.


# NSNoPenetrationBC

!syntax description /Modules/NavierStokes/BCs/NSNoPenetrationBC

## Overview

!! Replace these lines with information regarding the NSNoPenetrationBC object.

## Example Input File Syntax

!! Describe and include an example of how to use the NSNoPenetrationBC object.

!syntax parameters /Modules/NavierStokes/BCs/NSNoPenetrationBC

!syntax inputs /Modules/NavierStokes/BCs/NSNoPenetrationBC

!syntax children /Modules/NavierStokes/BCs/NSNoPenetrationBC

This class facilitates adding solid wall 'no penetration' BCs for the Euler equations.

Input Parameters

boundaryThe list of boundary IDs from the mesh where this boundary condition applies
C++ Type:std::vector
Options:
Description:The list of boundary IDs from the mesh where this boundary condition applies
fluid_propertiesThe name of the user object for fluid properties
C++ Type:UserObjectName
Options:
Description:The name of the user object for fluid properties

Required Parameters

control_tagsAdds user-defined labels for accessing object parameters via control logic.
C++ Type:std::vector
Options:
Description:Adds user-defined labels for accessing object parameters via control logic.
enableTrueSet the enabled status of the MooseObject.
Default:True
C++ Type:bool
Options:
Description:Set the enabled status of the MooseObject.

Advanced Parameters

Input Files

modules/navier_stokes/test/tests/step/step.i
modules/navier_stokes/test/tests/bump/bump.i

modules/navier_stokes/test/tests/step/step.i

# Navier-Stokes (or Euler) flow of an ideal gas over a step.
#
# Note: this problem is not currently a regression test for the
# Navier-Stokes module since it is in some sense ill-posed.  As
# discussed in [0], the sharp corner of the step (both forward and
# backward-facing) introduces a singularity in the first derivative of
# the velocity and pressure fields, and therefore produces large
# numerical errors in the neighborhood of these points.  Physically,
# this numerical error can be interpreted as causing an artificial
# "boundary layer" to form just above the step, as well as a spurious
# production of entropy even though the flow remains subsonic.
# Nevertheless, the forward-facing step problem in particular remains
# a challenging and well-document test problem for flow solvers, and
# this input file is included to help facilitate its development and
# employment by users of the module.
#
# [0]: Woodward and Colella, "The numerical simulation of
# two-dimenstional fluid flow with strong shocks," Journal of
# Computational Physics 54(1), pp. 115-173, 1984

[Mesh]
  type = FileMesh
  file = step.e
  dim = 2
  # uniform_refine = 3
[]


[Modules]
  [./FluidProperties]
    [./ideal_gas]
      type = IdealGasFluidProperties
      gamma = 1.4
      R = 287
    [../]
  [../]

  [./NavierStokes]
    [./Variables]
      #         'rho rhou rhov   rhoE'
      scaling = '1.  1.    1.    9.869232667160121e-6'
      family = LAGRANGE
      order = FIRST
    [../]

    [./ICs]
      initial_pressure = 101325.
      initial_temperature = 300.
      initial_velocity = '173.594354746921 0 0' # Mach 0.5: = 0.5*sqrt(gamma*R*T)
      fluid_properties = ideal_gas
    [../]

    [./Kernels]
      fluid_properties = ideal_gas
    [../]

    [./BCs]
      [./inlet]
        type = NSWeakStagnationInletBC
        boundary = 'left'
        stagnation_pressure = 120192.995549849 # Pa, Mach=0.5 at 1 atm
        stagnation_temperature = 315 # K, Mach=0.5 at 1 atm
        sx = 1.
        sy = 0.
        fluid_properties = ideal_gas
      [../]

      [./solid_walls]
        type = NSNoPenetrationBC
        boundary = 'top bottom step_top step_left step_right'
        fluid_properties = ideal_gas
      [../]

      [./outlet]
        type = NSStaticPressureOutletBC
        boundary = 'right'
        specified_pressure = 101325 # Pa
        fluid_properties = ideal_gas
      [../]
    [../]
  [../]
[]



[Materials]
  [./fluid]
    type = Air
    block = 1
    rho = rho
    rhou = rhou
    rhov = rhov
    rhoE = rhoE
    vel_x = vel_x
    vel_y = vel_y
    temperature = temperature
    enthalpy = enthalpy
    # This value is not used in the Euler equations, but it *is* used
    # by the stabilization parameter computation, which it decreases
    # the amount of artificial viscosity added, so it's best to use a
    # realistic value.
    dynamic_viscosity = 0.0
    fluid_properties = ideal_gas
  [../]
[]



[Preconditioning]
  [./SMP_PJFNK]
    type = SMP
    full = true
    solve_type = 'PJFNK'
  [../]
[]



[Executioner]
  type = Transient
  dt = 5.e-5
  dtmin = 1.e-5
  start_time = 0.0
  num_steps = 10000
  nl_rel_tol = 1e-5
  nl_abs_tol = 1e-9
  # nl_abs_step_tol = 1e-15
  nl_max_its = 5
  l_tol = 1e-4 # Relative linear tolerance for each Krylov solve
  l_max_its = 100 # Number of linear iterations for each Krylov solve

  # Specify the order as FIRST, otherwise you will get warnings in DEBUG mode...
  [./Quadrature]
    type = TRAP
    order = FIRST
  [../]
[]



[Outputs]
  file_base = step_out
  interval = 1
  exodus = true
[]

modules/navier_stokes/test/tests/bump/bump.i

# Euler flow of an ideal gas over a Gaussian "bump".
#
# The inlet is a stagnation pressure and temperature BC which
# corresponds to subsonic (M=0.5) flow with a static pressure of 1 atm
# and static temperature of 300K.  The outlet consists of a
# weakly-imposed static pressure BC of 1 atm.  The top and bottom
# walls of the channel weakly impose the "no normal flow" BC. The
# problem is initialized with freestream flow throughout the domain.
# Although this initial condition is less physically realistic, it
# helps the problem reach steady state more quickly.
#
# There is a sequence of uniformly-refined, geometry-fitted meshes
# from Yidong Xia available for solving this classical subsonic test
# problem (see the Mesh block below).  A coarse grid is used for the
# actual regression test, but changing one line in the Mesh block is
# sufficient to run this problem with different meshes.  An
# entropy-based error estimate is also provided, and can be used to
# demonstrate convergence of the numerical solution (since the true
# solution should produce zero entropy).  The error should converge at
# second-order in this norm.
[Mesh]
  # Bi-Linear elements
  # file = SmoothBump_quad_ref1_Q1.msh # 84 elems, 65 nodes
  # file = SmoothBump_quad_ref2_Q1.msh # 192 elems, 225 nodes
  # file = SmoothBump_quad_ref3_Q1.msh # 768 elems, 833 nodes
  # file = SmoothBump_quad_ref4_Q1.msh # 3072 elems, 3201 nodes
  # file = SmoothBump_quad_ref5_Q1.msh # 12288 elems, 12545 nodes
  # Bi-Quadratic elements
  # file = SmoothBump_quad_ref0_Q2.msh # 32 elems, 65 nodes
  # file = SmoothBump_quad_ref1_Q2.msh # 84 elems, 225 nodes
  file = SmoothBump_quad_ref2_Q2.msh # 260 elems, 833 nodes
  # file = SmoothBump_quad_ref3_Q2.msh # 900 elems, 3201 nodes
  # file = SmoothBump_quad_ref4_Q2.msh # 3332 elems, 12545 nodes
  # file = SmoothBump_quad_ref5_Q2.msh # 12804 elems, 49665 nodes
[]



[Modules]
  [./FluidProperties]
    [./ideal_gas]
      type = IdealGasFluidProperties
      gamma = 1.4
      molar_mass = 0.02897024320557491
    [../]
  [../]

  [./NavierStokes]
    [./Variables]
      #         'rho rhou rhov   rhoE'
      scaling = '1.  1.    1.    9.869232667160121e-6'
      family = LAGRANGE
      order = FIRST
    [../]

    [./ICs]
      initial_pressure = 101325.
      initial_temperature = 300.
      initial_velocity = '173.594354746921 0 0' # Mach 0.5: = 0.5*sqrt(gamma*R*T)
      fluid_properties = ideal_gas
    [../]

    [./Kernels]
      fluid_properties = ideal_gas
    [../]

    [./BCs]
      [./inlet]
        type = NSWeakStagnationInletBC
        boundary = '1'
        stagnation_pressure = 120192.995549849 # Pa, Mach=0.5 at 1 atm
        stagnation_temperature = 315 # K, Mach=0.5 at 1 atm
        sx = 1.
        sy = 0.
        fluid_properties = ideal_gas
      [../]

      [./solid_walls]
        type = NSNoPenetrationBC
        boundary = '3 4' # 'Lower Wall, Upper Wall'
        fluid_properties = ideal_gas
      [../]

      [./outlet]
        type = NSStaticPressureOutletBC
        boundary = '2' # 'Outflow'
        specified_pressure = 101325 # Pa
        fluid_properties = ideal_gas
      [../]
    [../]
  [../]
[]



[Materials]
  [./fluid]
    type = Air
    block = 0 # 'MeshInterior'
    rho = rho
    rhou = rhou
    rhov = rhov
    rhoE = rhoE
    vel_x = vel_x
    vel_y = vel_y
    temperature = temperature
    enthalpy = enthalpy
    # This value is not used in the Euler equations, but it *is* used
    # by the stabilization parameter computation, which it decreases
    # the amount of artificial viscosity added, so it's best to use a
    # realistic value.
    dynamic_viscosity = 0.0
    fluid_properties = ideal_gas
  [../]
[]



[Postprocessors]
  [./entropy_error]
    type = NSEntropyError
    execute_on = 'initial timestep_end'
    block = 0
    rho_infty = 1.1768292682926829
    p_infty = 101325
    rho = rho
    pressure = pressure
    fluid_properties = ideal_gas
  [../]
[]



[Preconditioning]
  [./SMP_PJFNK]
    type = SMP
    full = true
    solve_type = 'PJFNK'
  [../]
[]



[Executioner]
  type = Transient
  dt = 5.e-5
  dtmin = 1.e-5
  start_time = 0.0
  num_steps = 10
  nl_rel_tol = 1e-9
  nl_max_its = 5
  l_tol = 1e-4
  l_max_its = 100

  # We use trapezoidal quadrature.  This improves stability by
  # mimicking the "group variable" discretization approach.
  [./Quadrature]
    type = TRAP
    order = FIRST
  [../]
[]



[Outputs]
  interval = 1
  exodus = true
[]

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NSNoPenetrationBC

Input Parameters

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