#### 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
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 = '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
[]
```