def main():
'''This program runs SU2 and ensures that the output matches specified values.
This will be used to do checks when code is pushed to github
to make sure nothing is broken. '''
test_list = []
##########################
### Compressible Euler ###
##########################
# Channel
channel = TestCase('channel')
channel.cfg_dir = "euler/channel"
channel.cfg_file = "inv_channel_RK.cfg"
channel.test_iter = 20
channel.test_vals = [-2.667328, 2.797437, 0.018714, 0.006906]
test_list.append(channel)
# NACA0012
naca0012 = TestCase('naca0012')
naca0012.cfg_dir = "euler/naca0012"
naca0012.cfg_file = "inv_NACA0012_Roe.cfg"
naca0012.test_iter = 20
naca0012.test_vals = [-4.023999, -3.515034, 0.339426, 0.022217]
test_list.append(naca0012)
# Supersonic wedge
wedge = TestCase('wedge')
wedge.cfg_dir = "euler/wedge"
wedge.cfg_file = "inv_wedge_HLLC.cfg"
wedge.test_iter = 20
wedge.test_vals = [-0.942862, 4.784581, -0.208106, 0.036665]
test_list.append(wedge)
# ONERA M6 Wing
oneram6 = TestCase('oneram6')
oneram6.cfg_dir = "euler/oneram6"
oneram6.cfg_file = "inv_ONERAM6.cfg"
oneram6.test_iter = 10
oneram6.test_vals = [0.281703, 0.011821]
test_list.append(oneram6)
# Fixed CL NACA0012
fixedCL_naca0012 = TestCase('fixedcl_naca0012')
fixedCL_naca0012.cfg_dir = "fixed_cl/naca0012"
fixedCL_naca0012.cfg_file = "inv_NACA0012.cfg"
fixedCL_naca0012.test_iter = 10
fixedCL_naca0012.test_vals = [-7.374806, -1.872330, 0.300000, 0.019471]
test_list.append(fixedCL_naca0012)
# HYPERSONIC FLOW PAST BLUNT BODY
bluntbody = TestCase('bluntbody')
bluntbody.cfg_dir = "euler/bluntbody"
bluntbody.cfg_file = "blunt.cfg"
bluntbody.test_iter = 20
bluntbody.test_vals = [0.540010, 6.916656, 0.000027, 1.869004]
test_list.append(bluntbody)
##########################
### Compressible N-S ###
##########################
# Laminar flat plate
flatplate = TestCase('flatplate')
flatplate.cfg_dir = "navierstokes/flatplate"
flatplate.cfg_file = "lam_flatplate.cfg"
flatplate.test_iter = 20
flatplate.test_vals = [
-4.680775, 0.781235, -0.135957, 0.022978, 2.8549e-03, 2.3621e+00,
-2.3592e+00
]
test_list.append(flatplate)
# Laminar cylinder (steady)
cylinder = TestCase('cylinder')
cylinder.cfg_dir = "navierstokes/cylinder"
cylinder.cfg_file = "lam_cylinder.cfg"
cylinder.test_iter = 25
cylinder.test_vals = [-6.765429, -1.297425, 0.019571, 0.310232]
test_list.append(cylinder)
# Laminar cylinder (low Mach correction)
cylinder_lowmach = TestCase('cylinder_lowmach')
cylinder_lowmach.cfg_dir = "navierstokes/cylinder"
cylinder_lowmach.cfg_file = "cylinder_lowmach.cfg"
cylinder_lowmach.test_iter = 25
cylinder_lowmach.test_vals = [-6.850130, -1.388096, -0.056036, 108.140811]
test_list.append(cylinder_lowmach)
# 2D Poiseuille flow (body force driven with periodic inlet / outlet)
poiseuille = TestCase('poiseuille')
poiseuille.cfg_dir = "navierstokes/poiseuille"
poiseuille.cfg_file = "lam_poiseuille.cfg"
poiseuille.test_iter = 10
poiseuille.test_vals = [-5.048282, 0.650814, 0.008714, 13.677678]
test_list.append(poiseuille)
# 2D Poiseuille flow (inlet profile file)
poiseuille_profile = TestCase('poiseuille_profile')
poiseuille_profile.cfg_dir = "navierstokes/poiseuille"
poiseuille_profile.cfg_file = "profile_poiseuille.cfg"
poiseuille_profile.test_iter = 10
poiseuille_profile.test_vals = [-12.494752, -7.712204, -0.000000, 2.085796]
test_list.append(poiseuille_profile)
##########################
### Compressible RANS ###
##########################
# RAE2822 SA
rae2822_sa = TestCase('rae2822_sa')
rae2822_sa.cfg_dir = "rans/rae2822"
rae2822_sa.cfg_file = "turb_SA_RAE2822.cfg"
rae2822_sa.test_iter = 20
rae2822_sa.test_vals = [-2.020123, -5.269330, 0.807147, 0.060499]
test_list.append(rae2822_sa)
# RAE2822 SST
rae2822_sst = TestCase('rae2822_sst')
rae2822_sst.cfg_dir = "rans/rae2822"
rae2822_sst.cfg_file = "turb_SST_RAE2822.cfg"
rae2822_sst.test_iter = 20
rae2822_sst.test_vals = [-0.510635, 4.871104, 0.811904, 0.061614]
test_list.append(rae2822_sst)
# RAE2822 SST_SUST
rae2822_sst_sust = TestCase('rae2822_sst_sust')
rae2822_sst_sust.cfg_dir = "rans/rae2822"
rae2822_sst_sust.cfg_file = "turb_SST_SUST_RAE2822.cfg"
rae2822_sst_sust.test_iter = 20
rae2822_sst_sust.test_vals = [-2.430589, 4.871104, 0.811903, 0.061614]
test_list.append(rae2822_sst_sust)
# Flat plate
turb_flatplate = TestCase('turb_flatplate')
turb_flatplate.cfg_dir = "rans/flatplate"
turb_flatplate.cfg_file = "turb_SA_flatplate.cfg"
turb_flatplate.test_iter = 20
turb_flatplate.test_vals = [-4.157169, -6.737133, -0.176253, 0.057446]
test_list.append(turb_flatplate)
# ONERA M6 Wing
turb_oneram6 = TestCase('turb_oneram6')
turb_oneram6.cfg_dir = "rans/oneram6"
turb_oneram6.cfg_file = "turb_ONERAM6.cfg"
turb_oneram6.test_iter = 10
turb_oneram6.test_vals = [-2.388836, -6.689414, 0.230320, 0.157640]
test_list.append(turb_oneram6)
# NACA0012 (SA, FUN3D finest grid results: CL=1.0983, CD=0.01242)
turb_naca0012_sa = TestCase('turb_naca0012_sa')
turb_naca0012_sa.cfg_dir = "rans/naca0012"
turb_naca0012_sa.cfg_file = "turb_NACA0012_sa.cfg"
turb_naca0012_sa.test_iter = 10
turb_naca0012_sa.test_vals = [
-8.627052, -10.377936, 1.064491, 0.019710, 20.000000, -1.763095,
20.000000, -4.794176
]
test_list.append(turb_naca0012_sa)
# NACA0012 (SST, FUN3D finest grid results: CL=1.0840, CD=0.01253)
turb_naca0012_sst = TestCase('turb_naca0012_sst')
turb_naca0012_sst.cfg_dir = "rans/naca0012"
turb_naca0012_sst.cfg_file = "turb_NACA0012_sst.cfg"
turb_naca0012_sst.test_iter = 10
turb_naca0012_sst.test_vals = [
-11.450475, -12.797872, -5.863655, 1.049989, 0.019163, -1.856263
]
test_list.append(turb_naca0012_sst)
# NACA0012 (SST_SUST, FUN3D finest grid results: CL=1.0840, CD=0.01253)
turb_naca0012_sst_sust = TestCase('turb_naca0012_sst_sust')
turb_naca0012_sst_sust.cfg_dir = "rans/naca0012"
turb_naca0012_sst_sust.cfg_file = "turb_NACA0012_sst_sust.cfg"
turb_naca0012_sst_sust.test_iter = 10
turb_naca0012_sst_sust.test_vals = [
-11.367051, -12.640670, -5.746919, 1.005233, 0.019017, -1.913905
]
test_list.append(turb_naca0012_sst_sust)
# NACA0012 (SST, fixed values for turbulence quantities)
turb_naca0012_sst_fixedvalues = TestCase('turb_naca0012_sst_fixedvalues')
turb_naca0012_sst_fixedvalues.cfg_dir = "rans/naca0012"
turb_naca0012_sst_fixedvalues.cfg_file = "turb_NACA0012_sst_fixedvalues.cfg"
turb_naca0012_sst_fixedvalues.test_iter = 10
turb_naca0012_sst_fixedvalues.test_vals = [
-5.192502, -9.575898, -1.568269, 1.022571, 0.040527, -2.384329
]
test_list.append(turb_naca0012_sst_fixedvalues)
# NACA0012 (SST, explicit Euler for flow and turbulence equations)
turb_naca0012_sst_expliciteuler = TestCase(
'turb_naca0012_sst_expliciteuler')
turb_naca0012_sst_expliciteuler.cfg_dir = "rans/naca0012"
turb_naca0012_sst_expliciteuler.cfg_file = "turb_NACA0012_sst_expliciteuler.cfg"
turb_naca0012_sst_expliciteuler.test_iter = 10
turb_naca0012_sst_expliciteuler.test_vals = [
-3.532228, -3.157766, 3.364025, 1.124824, 0.501717, -float("inf")
]
test_list.append(turb_naca0012_sst_expliciteuler)
# PROPELLER
propeller = TestCase('propeller')
propeller.cfg_dir = "rans/propeller"
propeller.cfg_file = "propeller.cfg"
propeller.test_iter = 10
propeller.test_vals = [-3.389575, -8.409529, 0.000048, 0.056329]
test_list.append(propeller)
#######################################
### Axisymmetric Compressible RANS ###
#######################################
# Axisymmetric air nozzle (transonic)
axi_rans_air_nozzle = TestCase('axi_rans_air_nozzle')
axi_rans_air_nozzle.cfg_dir = "axisymmetric_rans/air_nozzle"
axi_rans_air_nozzle.cfg_file = "air_nozzle.cfg"
axi_rans_air_nozzle.test_iter = 10
axi_rans_air_nozzle.test_vals = [
-12.093575, -6.630426, -8.798725, -2.399130
]
test_list.append(axi_rans_air_nozzle)
#################################
## Compressible RANS Restart ###
#################################
# NACA0012 SST Multigrid restart
turb_naca0012_sst_restart_mg = TestCase('turb_naca0012_sst_restart_mg')
turb_naca0012_sst_restart_mg.cfg_dir = "rans/naca0012"
turb_naca0012_sst_restart_mg.cfg_file = "turb_NACA0012_sst_multigrid_restart.cfg"
turb_naca0012_sst_restart_mg.test_iter = 20
turb_naca0012_sst_restart_mg.ntest_vals = 5
turb_naca0012_sst_restart_mg.test_vals = [
-7.652987, -7.729472, -1.981061, -0.000015, 0.079061
]
test_list.append(turb_naca0012_sst_restart_mg)
#############################
### Compressibele RANS UQ ###
#############################
# NACA0012 1c
turb_naca0012_1c = TestCase('turb_naca0012_1c')
turb_naca0012_1c.cfg_dir = "rans_uq/naca0012"
turb_naca0012_1c.cfg_file = "turb_NACA0012_uq_1c.cfg"
turb_naca0012_1c.test_iter = 10
turb_naca0012_1c.test_vals = [-4.980749, 1.139261, 0.244644, -0.112857]
test_list.append(turb_naca0012_1c)
# NACA0012 2c
turb_naca0012_2c = TestCase('turb_naca0012_2c')
turb_naca0012_2c.cfg_dir = "rans_uq/naca0012"
turb_naca0012_2c.cfg_file = "turb_NACA0012_uq_2c.cfg"
turb_naca0012_2c.test_iter = 10
turb_naca0012_2c.test_vals = [-5.483337, 0.968887, 0.212057, -0.120310]
test_list.append(turb_naca0012_2c)
# NACA0012 3c
turb_naca0012_3c = TestCase('turb_naca0012_3c')
turb_naca0012_3c.cfg_dir = "rans_uq/naca0012"
turb_naca0012_3c.cfg_file = "turb_NACA0012_uq_3c.cfg"
turb_naca0012_3c.test_iter = 10
turb_naca0012_3c.test_vals = [-5.584300, 0.931383, 0.205113, -0.120892]
test_list.append(turb_naca0012_3c)
# NACA0012 p1c1
turb_naca0012_p1c1 = TestCase('turb_naca0012_p1c1')
turb_naca0012_p1c1.cfg_dir = "rans_uq/naca0012"
turb_naca0012_p1c1.cfg_file = "turb_NACA0012_uq_p1c1.cfg"
turb_naca0012_p1c1.test_iter = 10
turb_naca0012_p1c1.test_vals = [-5.133233, 1.075372, 0.337556, -0.077868]
test_list.append(turb_naca0012_p1c1)
# NACA0012 p1c2
turb_naca0012_p1c2 = TestCase('turb_naca0012_p1c2')
turb_naca0012_p1c2.cfg_dir = "rans_uq/naca0012"
turb_naca0012_p1c2.cfg_file = "turb_NACA0012_uq_p1c2.cfg"
turb_naca0012_p1c2.test_iter = 10
turb_naca0012_p1c2.test_vals = [-5.554619, 0.943693, 0.226386, -0.116553]
test_list.append(turb_naca0012_p1c2)
######################################
### Harmonic Balance ###
######################################
# Description of the regression test
harmonic_balance = TestCase('harmonic_balance')
harmonic_balance.cfg_dir = "harmonic_balance"
harmonic_balance.cfg_file = "HB.cfg"
harmonic_balance.test_iter = 25
harmonic_balance.test_vals = [-1.589740, 3.922578, 0.006703, 0.099632]
harmonic_balance.new_output = False
test_list.append(harmonic_balance)
# Turbulent pitching NACA 64a010 airfoil
hb_rans_preconditioning = TestCase('hb_rans_preconditioning')
hb_rans_preconditioning.cfg_dir = "harmonic_balance/hb_rans_preconditioning"
hb_rans_preconditioning.cfg_file = "davis.cfg"
hb_rans_preconditioning.test_iter = 25
hb_rans_preconditioning.test_vals = [
-1.902111, -5.949288, 0.007768, 0.128060
]
hb_rans_preconditioning.new_output = False
test_list.append(hb_rans_preconditioning)
#############################
### Incompressible Euler ###
#############################
# NACA0012 Hydrofoil
inc_euler_naca0012 = TestCase('inc_euler_naca0012')
inc_euler_naca0012.cfg_dir = "incomp_euler/naca0012"
inc_euler_naca0012.cfg_file = "incomp_NACA0012.cfg"
inc_euler_naca0012.test_iter = 20
inc_euler_naca0012.test_vals = [-4.858287, -3.810487, 0.491850, 0.007002]
inc_euler_naca0012.new_output = True
test_list.append(inc_euler_naca0012)
# C-D nozzle with pressure inlet and mass flow outlet
inc_nozzle = TestCase('inc_nozzle')
inc_nozzle.cfg_dir = "incomp_euler/nozzle"
inc_nozzle.cfg_file = "inv_nozzle.cfg"
inc_nozzle.test_iter = 20
inc_nozzle.test_vals = [-5.971249, -4.910844, -0.000196, 0.121635]
inc_nozzle.new_output = True
test_list.append(inc_nozzle)
#############################
### Incompressible N-S ###
#############################
# Laminar cylinder
inc_lam_cylinder = TestCase('inc_lam_cylinder')
inc_lam_cylinder.cfg_dir = "incomp_navierstokes/cylinder"
inc_lam_cylinder.cfg_file = "incomp_cylinder.cfg"
inc_lam_cylinder.test_iter = 10
inc_lam_cylinder.test_vals = [-4.004277, -3.227956, 0.003851, 7.626583]
inc_lam_cylinder.new_output = True
test_list.append(inc_lam_cylinder)
# Buoyancy-driven cavity
inc_buoyancy = TestCase('inc_buoyancy')
inc_buoyancy.cfg_dir = "incomp_navierstokes/buoyancy_cavity"
inc_buoyancy.cfg_file = "lam_buoyancy_cavity.cfg"
inc_buoyancy.test_iter = 20
inc_buoyancy.test_vals = [-4.432484, 0.507522, 0.000000, 0.000000]
inc_buoyancy.new_output = True
test_list.append(inc_buoyancy)
# Laminar heated cylinder with polynomial fluid model
inc_poly_cylinder = TestCase('inc_poly_cylinder')
inc_poly_cylinder.cfg_dir = "incomp_navierstokes/cylinder"
inc_poly_cylinder.cfg_file = "poly_cylinder.cfg"
inc_poly_cylinder.test_iter = 20
inc_poly_cylinder.test_vals = [-7.851512, -2.093420, 0.029974, 1.921595]
inc_poly_cylinder.new_output = True
test_list.append(inc_poly_cylinder)
# X-coarse laminar bend as a mixed element CGNS test
inc_lam_bend = TestCase('inc_lam_bend')
inc_lam_bend.cfg_dir = "incomp_navierstokes/bend"
inc_lam_bend.cfg_file = "lam_bend.cfg"
inc_lam_bend.test_iter = 10
inc_lam_bend.test_vals = [-3.436191, -3.098014, -0.017338, -0.193981]
test_list.append(inc_lam_bend)
############################
### Incompressible RANS ###
############################
# NACA0012, SA
inc_turb_naca0012 = TestCase('inc_turb_naca0012')
inc_turb_naca0012.cfg_dir = "incomp_rans/naca0012"
inc_turb_naca0012.cfg_file = "naca0012.cfg"
inc_turb_naca0012.test_iter = 20
inc_turb_naca0012.test_vals = [-4.788405, -11.040493, 0.000008, 0.309506]
inc_turb_naca0012.new_output = True
test_list.append(inc_turb_naca0012)
# NACA0012, SST_SUST
inc_turb_naca0012_sst_sust = TestCase('inc_turb_naca0012_sst_sust')
inc_turb_naca0012_sst_sust.cfg_dir = "incomp_rans/naca0012"
inc_turb_naca0012_sst_sust.cfg_file = "naca0012_SST_SUST.cfg"
inc_turb_naca0012_sst_sust.test_iter = 20
inc_turb_naca0012_sst_sust.test_vals = [
-7.276424, 0.145860, 0.000003, 0.312011
]
test_list.append(inc_turb_naca0012_sst_sust)
######################################
### Moving Wall ###
######################################
# Lid-driven cavity
cavity = TestCase('cavity')
cavity.cfg_dir = "moving_wall/cavity"
cavity.cfg_file = "lam_cavity.cfg"
cavity.test_iter = 25
cavity.test_vals = [-5.627934, -0.164469, 0.052000, 2.547063]
test_list.append(cavity)
# Spinning cylinder
spinning_cylinder = TestCase('spinning_cylinder')
spinning_cylinder.cfg_dir = "moving_wall/spinning_cylinder"
spinning_cylinder.cfg_file = "spinning_cylinder.cfg"
spinning_cylinder.test_iter = 25
spinning_cylinder.test_vals = [-8.001289, -2.607956, 1.501322, 1.488559]
test_list.append(spinning_cylinder)
######################################
### Unsteady ###
######################################
# Square cylinder
square_cylinder = TestCase('square_cylinder')
square_cylinder.cfg_dir = "unsteady/square_cylinder"
square_cylinder.cfg_file = "turb_square.cfg"
square_cylinder.test_iter = 3
square_cylinder.test_vals = [-1.162564, 0.066401, 1.399788, 2.220402]
square_cylinder.unsteady = True
test_list.append(square_cylinder)
# Gust
sine_gust = TestCase('sine_gust')
sine_gust.cfg_dir = "gust"
sine_gust.cfg_file = "inv_gust_NACA0012.cfg"
sine_gust.test_iter = 5
sine_gust.test_vals = [-1.977520, 3.481804, -0.012402, -0.007454]
sine_gust.unsteady = True
test_list.append(sine_gust)
# Aeroelastic
aeroelastic = TestCase('aeroelastic')
aeroelastic.cfg_dir = "aeroelastic"
aeroelastic.cfg_file = "aeroelastic_NACA64A010.cfg"
aeroelastic.test_iter = 2
aeroelastic.test_vals = [0.074433, 0.033108, -0.001650, -0.000127]
aeroelastic.unsteady = True
test_list.append(aeroelastic)
# Delayed Detached Eddy Simulation
ddes_flatplate = TestCase('ddes_flatplate')
ddes_flatplate.cfg_dir = "ddes/flatplate"
ddes_flatplate.cfg_file = "ddes_flatplate.cfg"
ddes_flatplate.test_iter = 10
ddes_flatplate.test_vals = [-2.714758, -5.883004, -0.215005, 0.023783]
ddes_flatplate.unsteady = True
test_list.append(ddes_flatplate)
# unsteady pitching NACA0015, SA
unst_inc_turb_naca0015_sa = TestCase('unst_inc_turb_naca0015_sa')
unst_inc_turb_naca0015_sa.cfg_dir = "unsteady/pitching_naca0015_rans_inc"
unst_inc_turb_naca0015_sa.cfg_file = "config_incomp_turb_sa.cfg"
unst_inc_turb_naca0015_sa.test_iter = 1
unst_inc_turb_naca0015_sa.test_vals = [
-3.008629, -6.888974, 1.435193, 0.433537
]
unst_inc_turb_naca0015_sa.unsteady = True
test_list.append(unst_inc_turb_naca0015_sa)
# unsteady pitching NACA0012, Euler, Deforming
unst_deforming_naca0012 = TestCase('unst_deforming_naca0012')
unst_deforming_naca0012.cfg_dir = "disc_adj_euler/naca0012_pitching_def"
unst_deforming_naca0012.cfg_file = "inv_NACA0012_pitching_deform.cfg"
unst_deforming_naca0012.test_iter = 5
unst_deforming_naca0012.test_vals = [
-3.665120, -3.793643, -3.716518, -3.148310
]
unst_deforming_naca0012.unsteady = True
test_list.append(unst_deforming_naca0012)
######################################
### NICFD ###
######################################
# Rarefaction shock wave edge_VW
edge_VW = TestCase('edge_VW')
edge_VW.cfg_dir = "nicf/edge"
edge_VW.cfg_file = "edge_VW.cfg"
edge_VW.test_iter = 100
edge_VW.test_vals = [-5.040287, 1.124488, -0.000009, 0.000000]
test_list.append(edge_VW)
# Rarefaction shock wave edge_PPR
edge_PPR = TestCase('edge_PPR')
edge_PPR.cfg_dir = "nicf/edge"
edge_PPR.cfg_file = "edge_PPR.cfg"
edge_PPR.test_iter = 100
edge_PPR.test_vals = [-5.401601, 0.738205, -0.000035, 0.000000]
test_list.append(edge_PPR)
######################################
### Turbomachinery ###
######################################
# Jones APU Turbocharger
Jones_tc = TestCase('jones_turbocharger')
Jones_tc.cfg_dir = "turbomachinery/APU_turbocharger"
Jones_tc.cfg_file = "Jones.cfg"
Jones_tc.test_iter = 5
Jones_tc.test_vals = [-5.279930, 0.379651, 72.212100, 1.277439]
Jones_tc.new_output = False
test_list.append(Jones_tc)
# Jones APU Turbocharger restart
Jones_tc_rst = TestCase('jones_turbocharger_restart')
Jones_tc_rst.cfg_dir = "turbomachinery/APU_turbocharger"
Jones_tc_rst.cfg_file = "Jones_rst.cfg"
Jones_tc_rst.test_iter = 5
Jones_tc_rst.test_vals = [-4.625251, -1.568824, 33.995140, 10.181940]
Jones_tc_rst.new_output = False
test_list.append(Jones_tc_rst)
# 2D axial stage
axial_stage2D = TestCase('axial_stage2D')
axial_stage2D.cfg_dir = "turbomachinery/axial_stage_2D"
axial_stage2D.cfg_file = "Axial_stage2D.cfg"
axial_stage2D.test_iter = 20
axial_stage2D.test_vals = [-1.933139, 5.380376, 73.357910, 0.925874]
axial_stage2D.new_output = False
test_list.append(axial_stage2D)
# 2D transonic stator
transonic_stator = TestCase('transonic_stator')
transonic_stator.cfg_dir = "turbomachinery/transonic_stator_2D"
transonic_stator.cfg_file = "transonic_stator.cfg"
transonic_stator.test_iter = 20
transonic_stator.test_vals = [-0.565608, 5.833408, 96.476150, 0.062517]
transonic_stator.new_output = False
test_list.append(transonic_stator)
# 2D transonic stator restart
transonic_stator_rst = TestCase('transonic_stator_restart')
transonic_stator_rst.cfg_dir = "turbomachinery/transonic_stator_2D"
transonic_stator_rst.cfg_file = "transonic_stator_rst.cfg"
transonic_stator_rst.test_iter = 20
transonic_stator_rst.test_vals = [-6.619122, -0.615716, 5.002986, 0.002951]
transonic_stator_rst.new_output = False
test_list.append(transonic_stator_rst)
######################################
### Sliding Mesh ###
######################################
# Uniform flow
uniform_flow = TestCase('uniform_flow')
uniform_flow.cfg_dir = "sliding_interface/uniform_flow"
uniform_flow.cfg_file = "uniform_NN.cfg"
uniform_flow.test_iter = 5
uniform_flow.test_vals = [5.000000, 0.000000, -0.188748, -10.631524]
uniform_flow.unsteady = True
uniform_flow.multizone = True
test_list.append(uniform_flow)
# Channel_2D
channel_2D = TestCase('channel_2D')
channel_2D.cfg_dir = "sliding_interface/channel_2D"
channel_2D.cfg_file = "channel_2D_WA.cfg"
channel_2D.test_iter = 2
channel_2D.test_vals = [2.000000, 0.000000, 0.397972, 0.352756, 0.405398]
channel_2D.unsteady = True
channel_2D.multizone = True
test_list.append(channel_2D)
# Channel_3D
channel_3D = TestCase('channel_3D')
channel_3D.cfg_dir = "sliding_interface/channel_3D"
channel_3D.cfg_file = "channel_3D_WA.cfg"
channel_3D.test_iter = 2
channel_3D.test_vals = [2.000000, 0.000000, 0.620171, 0.505178, 0.415313]
channel_3D.unsteady = True
channel_3D.multizone = True
test_list.append(channel_3D)
# Pipe
pipe = TestCase('pipe')
pipe.cfg_dir = "sliding_interface/pipe"
pipe.cfg_file = "pipe_NN.cfg"
pipe.test_iter = 2
pipe.test_vals = [0.150024, 0.491949, 0.677759, 0.963991, 1.006947]
pipe.unsteady = True
pipe.multizone = True
test_list.append(pipe)
# Rotating cylinders
rotating_cylinders = TestCase('rotating_cylinders')
rotating_cylinders.cfg_dir = "sliding_interface/rotating_cylinders"
rotating_cylinders.cfg_file = "rot_cylinders_WA.cfg"
rotating_cylinders.test_iter = 3
rotating_cylinders.test_vals = [
3.000000, 0.000000, 0.777568, 1.134807, 1.224137
]
rotating_cylinders.unsteady = True
rotating_cylinders.multizone = True
test_list.append(rotating_cylinders)
# Supersonic vortex shedding
supersonic_vortex_shedding = TestCase('supersonic_vortex_shedding')
supersonic_vortex_shedding.cfg_dir = "sliding_interface/supersonic_vortex_shedding"
supersonic_vortex_shedding.cfg_file = "sup_vor_shed_WA.cfg"
supersonic_vortex_shedding.test_iter = 5
supersonic_vortex_shedding.test_vals = [
5.000000, 0.000000, 1.216554, 1.639119
]
supersonic_vortex_shedding.unsteady = True
supersonic_vortex_shedding.multizone = True
test_list.append(supersonic_vortex_shedding)
# Bars_SST_2D
bars_SST_2D = TestCase('bars_SST_2D')
bars_SST_2D.cfg_dir = "sliding_interface/bars_SST_2D"
bars_SST_2D.cfg_file = "bars.cfg"
bars_SST_2D.test_iter = 13
bars_SST_2D.test_vals = [13.000000, -0.619686, -1.564595]
bars_SST_2D.multizone = True
test_list.append(bars_SST_2D)
# Sliding mesh with incompressible flows (steady)
slinc_steady = TestCase('slinc_steady')
slinc_steady.cfg_dir = "sliding_interface/incompressible_steady"
slinc_steady.cfg_file = "config.cfg"
slinc_steady.test_iter = 19
slinc_steady.test_vals = [19.000000, -1.800401, -2.114687]
slinc_steady.multizone = True
test_list.append(slinc_steady)
##########################
### FEA - FSI ###
##########################
# Static beam, 3d
statbeam3d = TestCase('statbeam3d')
statbeam3d.cfg_dir = "fea_fsi/StatBeam_3d"
statbeam3d.cfg_file = "configBeam_3d.cfg"
statbeam3d.test_iter = 0
statbeam3d.test_vals = [-2.378370, -1.585252, -2.028505, 64359.000000]
test_list.append(statbeam3d)
# Dynamic beam, 2d
dynbeam2d = TestCase('dynbeam2d')
dynbeam2d.cfg_dir = "fea_fsi/DynBeam_2d"
dynbeam2d.cfg_file = "configBeam_2d.cfg"
dynbeam2d.test_iter = 6
dynbeam2d.test_vals = [-3.240015, 2.895057, -0.353146, 66127.000000]
dynbeam2d.unsteady = True
test_list.append(dynbeam2d)
# FSI, 2d
fsi2d = TestCase('fsi2d')
fsi2d.cfg_dir = "fea_fsi/WallChannel_2d"
fsi2d.cfg_file = "configFSI.cfg"
fsi2d.test_iter = 4
fsi2d.test_vals = [4.000000, 0.000000, -3.743227, -4.133479]
fsi2d.multizone = True
fsi2d.unsteady = True
test_list.append(fsi2d)
# FSI, Static, 2D, new mesh solver
stat_fsi = TestCase('stat_fsi')
stat_fsi.cfg_dir = "fea_fsi/stat_fsi"
stat_fsi.cfg_file = "config.cfg"
stat_fsi.test_iter = 7
stat_fsi.test_vals = [-5.403596, -5.722583, 0.000000, 10.000000]
stat_fsi.multizone = True
test_list.append(stat_fsi)
# FSI, Dynamic, 2D, new mesh solver
dyn_fsi = TestCase('dyn_fsi')
dyn_fsi.cfg_dir = "fea_fsi/dyn_fsi"
dyn_fsi.cfg_file = "config.cfg"
dyn_fsi.test_iter = 4
dyn_fsi.test_vals = [-4.355806, -4.060582, 0.000000, 102.000000]
dyn_fsi.multizone = True
dyn_fsi.unsteady = True
test_list.append(dyn_fsi)
# FSI, Static, 2D, new mesh solver, restart
stat_fsi_restart = TestCase('stat_fsi_restart')
stat_fsi_restart.cfg_dir = "fea_fsi/stat_fsi"
stat_fsi_restart.cfg_file = "config_restart.cfg"
stat_fsi_restart.test_iter = 1
stat_fsi_restart.test_vals = [-3.474082, -4.242343, 0.000000, 37.000000]
stat_fsi_restart.multizone = True
test_list.append(stat_fsi_restart)
##############################################
### Method of Manufactured Solutions (MMS) ###
##############################################
# FVM, compressible, laminar N-S
mms_fvm_ns = TestCase('mms_fvm_ns')
mms_fvm_ns.cfg_dir = "mms/fvm_navierstokes"
mms_fvm_ns.cfg_file = "lam_mms_roe.cfg"
mms_fvm_ns.test_iter = 20
mms_fvm_ns.test_vals = [-2.851428, 2.192348, 0.000000, 0.000000]
test_list.append(mms_fvm_ns)
# FVM, incompressible, euler
mms_fvm_inc_euler = TestCase('mms_fvm_inc_euler')
mms_fvm_inc_euler.cfg_dir = "mms/fvm_incomp_euler"
mms_fvm_inc_euler.cfg_file = "inv_mms_jst.cfg"
mms_fvm_inc_euler.test_iter = 20
mms_fvm_inc_euler.test_vals = [-9.128033, -9.441406, 0.000000, 0.000000]
test_list.append(mms_fvm_inc_euler)
# FVM, incompressible, laminar N-S
mms_fvm_inc_ns = TestCase('mms_fvm_inc_ns')
mms_fvm_inc_ns.cfg_dir = "mms/fvm_incomp_navierstokes"
mms_fvm_inc_ns.cfg_file = "lam_mms_fds.cfg"
mms_fvm_inc_ns.test_iter = 20
mms_fvm_inc_ns.test_vals = [-7.414944, -7.631546, 0.000000, 0.000000]
test_list.append(mms_fvm_inc_ns)
######################################
### RUN TESTS ###
######################################
for test in test_list:
test.su2_exec = "SU2_CFD -t 2"
test.timeout = 600
test.tol = 1e-4
#end
pass_list = [test.run_test() for test in test_list]
# Tests summary
print('==================================================================')
print('Summary of the hybrid parallel tests')
print('python version:', sys.version)
for i, test in enumerate(test_list):
if (pass_list[i]):
print(' passed - %s' % test.tag)
else:
print('* FAILED - %s' % test.tag)
if all(pass_list):
sys.exit(0)
else:
sys.exit(1)
def main():
'''This program runs SU2 and ensures that the output matches specified values.
This will be used to do checks when code is pushed to github
to make sure nothing is broken. '''
test_list = []
##########################
### Compressible Euler ###
##########################
# Channel
channel = TestCase('channel')
channel.cfg_dir = "euler/channel"
channel.cfg_file = "inv_channel_RK.cfg"
channel.test_iter = 20
channel.test_vals = [-2.667326, 2.797439, 0.018717, 0.006906]
test_list.append(channel)
# NACA0012
naca0012 = TestCase('naca0012')
naca0012.cfg_dir = "euler/naca0012"
naca0012.cfg_file = "inv_NACA0012_Roe.cfg"
naca0012.test_iter = 20
naca0012.test_vals = [-4.023999, -3.515034, 0.339426, 0.022217]
test_list.append(naca0012)
# Supersonic wedge
wedge = TestCase('wedge')
wedge.cfg_dir = "euler/wedge"
wedge.cfg_file = "inv_wedge_HLLC.cfg"
wedge.test_iter = 20
wedge.test_vals = [-0.942862, 4.784581, -0.208106, 0.036665]
test_list.append(wedge)
# ONERA M6 Wing
oneram6 = TestCase('oneram6')
oneram6.cfg_dir = "euler/oneram6"
oneram6.cfg_file = "inv_ONERAM6.cfg"
oneram6.test_iter = 10
oneram6.test_vals = [0.281704, 0.011821]
test_list.append(oneram6)
# Fixed CL NACA0012
fixedCL_naca0012 = TestCase('fixedcl_naca0012')
fixedCL_naca0012.cfg_dir = "fixed_cl/naca0012"
fixedCL_naca0012.cfg_file = "inv_NACA0012.cfg"
fixedCL_naca0012.test_iter = 10
fixedCL_naca0012.test_vals = [-12.130189, -6.702728, 0.300000, 0.019470]
test_list.append(fixedCL_naca0012)
# HYPERSONIC FLOW PAST BLUNT BODY
bluntbody = TestCase('bluntbody')
bluntbody.cfg_dir = "euler/bluntbody"
bluntbody.cfg_file = "blunt.cfg"
bluntbody.test_iter = 20
bluntbody.test_vals = [0.540010, 6.916656, 0.000027, 1.869004]
test_list.append(bluntbody)
##########################
### Compressible N-S ###
##########################
# Laminar flat plate
flatplate = TestCase('flatplate')
flatplate.cfg_dir = "navierstokes/flatplate"
flatplate.cfg_file = "lam_flatplate.cfg"
flatplate.test_iter = 20
flatplate.test_vals = [-4.680775, 0.781235, -0.135957, 0.022978]
test_list.append(flatplate)
# Laminar cylinder (steady)
cylinder = TestCase('cylinder')
cylinder.cfg_dir = "navierstokes/cylinder"
cylinder.cfg_file = "lam_cylinder.cfg"
cylinder.test_iter = 25
cylinder.test_vals = [-6.765432, -1.297428, 0.019596, 0.310240]
test_list.append(cylinder)
# Laminar cylinder (low Mach correction)
cylinder_lowmach = TestCase('cylinder_lowmach')
cylinder_lowmach.cfg_dir = "navierstokes/cylinder"
cylinder_lowmach.cfg_file = "cylinder_lowmach.cfg"
cylinder_lowmach.test_iter = 25
cylinder_lowmach.test_vals = [-6.850130, -1.388096, -0.056203, 108.140819]
test_list.append(cylinder_lowmach)
# 2D Poiseuille flow (body force driven with periodic inlet / outlet)
poiseuille = TestCase('poiseuille')
poiseuille.cfg_dir = "navierstokes/poiseuille"
poiseuille.cfg_file = "lam_poiseuille.cfg"
poiseuille.test_iter = 10
poiseuille.test_vals = [-5.048282, 0.650814, 0.008714, 13.677678]
test_list.append(poiseuille)
# 2D Poiseuille flow (inlet profile file)
poiseuille_profile = TestCase('poiseuille_profile')
poiseuille_profile.cfg_dir = "navierstokes/poiseuille"
poiseuille_profile.cfg_file = "profile_poiseuille.cfg"
poiseuille_profile.test_iter = 10
poiseuille_profile.test_vals = [-12.494721, -7.712408, -0.000000, 2.085796]
test_list.append(poiseuille_profile)
##########################
### Compressible RANS ###
##########################
# RAE2822 SA
rae2822_sa = TestCase('rae2822_sa')
rae2822_sa.cfg_dir = "rans/rae2822"
rae2822_sa.cfg_file = "turb_SA_RAE2822.cfg"
rae2822_sa.test_iter = 20
rae2822_sa.test_vals = [-2.021224, -5.268445, 0.807582, 0.060731]
test_list.append(rae2822_sa)
# RAE2822 SST
rae2822_sst = TestCase('rae2822_sst')
rae2822_sst.cfg_dir = "rans/rae2822"
rae2822_sst.cfg_file = "turb_SST_RAE2822.cfg"
rae2822_sst.test_iter = 20
rae2822_sst.test_vals = [-0.510637, 4.876603, 0.812485, 0.061969]
test_list.append(rae2822_sst)
# RAE2822 SST_SUST
rae2822_sst_sust = TestCase('rae2822_sst_sust')
rae2822_sst_sust.cfg_dir = "rans/rae2822"
rae2822_sst_sust.cfg_file = "turb_SST_SUST_RAE2822.cfg"
rae2822_sst_sust.test_iter = 20
rae2822_sst_sust.test_vals = [-2.429813, 4.876602, 0.812485, 0.061969]
test_list.append(rae2822_sst_sust)
# Flat plate
turb_flatplate = TestCase('turb_flatplate')
turb_flatplate.cfg_dir = "rans/flatplate"
turb_flatplate.cfg_file = "turb_SA_flatplate.cfg"
turb_flatplate.test_iter = 20
turb_flatplate.test_vals = [-4.157169, -6.737133, -0.176253, 0.057446]
test_list.append(turb_flatplate)
# ONERA M6 Wing
turb_oneram6 = TestCase('turb_oneram6')
turb_oneram6.cfg_dir = "rans/oneram6"
turb_oneram6.cfg_file = "turb_ONERAM6.cfg"
turb_oneram6.test_iter = 10
turb_oneram6.test_vals = [-2.388851, -6.689340, 0.230320, 0.157649]
test_list.append(turb_oneram6)
# NACA0012 (SA, FUN3D finest grid results: CL=1.0983, CD=0.01242)
turb_naca0012_sa = TestCase('turb_naca0012_sa')
turb_naca0012_sa.cfg_dir = "rans/naca0012"
turb_naca0012_sa.cfg_file = "turb_NACA0012_sa.cfg"
turb_naca0012_sa.test_iter = 10
turb_naca0012_sa.test_vals = [-11.537781, -14.899750, 1.064330, 0.019756]
test_list.append(turb_naca0012_sa)
# NACA0012 (SST, FUN3D finest grid results: CL=1.0840, CD=0.01253)
turb_naca0012_sst = TestCase('turb_naca0012_sst')
turb_naca0012_sst.cfg_dir = "rans/naca0012"
turb_naca0012_sst.cfg_file = "turb_NACA0012_sst.cfg"
turb_naca0012_sst.test_iter = 10
turb_naca0012_sst.test_vals = [-12.797090, -5.872763, 1.049989, 0.019163]
test_list.append(turb_naca0012_sst)
# NACA0012 (SST_SUST, FUN3D finest grid results: CL=1.0840, CD=0.01253)
turb_naca0012_sst_sust = TestCase('turb_naca0012_sst_sust')
turb_naca0012_sst_sust.cfg_dir = "rans/naca0012"
turb_naca0012_sst_sust.cfg_file = "turb_NACA0012_sst_sust.cfg"
turb_naca0012_sst_sust.test_iter = 10
turb_naca0012_sst_sust.test_vals = [
-12.640091, -5.751854, 1.005233, 0.019017
]
test_list.append(turb_naca0012_sst_sust)
# PROPELLER
propeller = TestCase('propeller')
propeller.cfg_dir = "rans/propeller"
propeller.cfg_file = "propeller.cfg"
propeller.test_iter = 10
propeller.test_vals = [-3.389576, -8.409529, 0.000048, 0.056329]
test_list.append(propeller)
# PROPELLER VARIBLE LOAD
propeller_var_load = TestCase('propeller_variable_load')
propeller_var_load.cfg_dir = "rans/actuatordisk_variable_load"
propeller_var_load.cfg_file = "propeller_variable_load.cfg"
propeller_var_load.test_iter = 20
propeller_var_load.test_vals = [-1.808010, -4.535613, 0.000190, 0.172483]
test_list.append(propeller_var_load)
#################################
## Compressible RANS Restart ###
#################################
# NACA0012 SST Multigrid restart
turb_naca0012_sst_restart_mg = TestCase('turb_naca0012_sst_restart_mg')
turb_naca0012_sst_restart_mg.cfg_dir = "rans/naca0012"
turb_naca0012_sst_restart_mg.cfg_file = "turb_NACA0012_sst_multigrid_restart.cfg"
turb_naca0012_sst_restart_mg.test_iter = 20
turb_naca0012_sst_restart_mg.ntest_vals = 5
turb_naca0012_sst_restart_mg.test_vals = [
-7.653296, -7.729472, -1.981061, -0.000016, 0.079062
]
test_list.append(turb_naca0012_sst_restart_mg)
#############################
### Compressibele RANS UQ ###
#############################
# NACA0012 1c
turb_naca0012_1c = TestCase('turb_naca0012_1c')
turb_naca0012_1c.cfg_dir = "rans_uq/naca0012"
turb_naca0012_1c.cfg_file = "turb_NACA0012_uq_1c.cfg"
turb_naca0012_1c.test_iter = 10
turb_naca0012_1c.test_vals = [-4.979389, 1.140070, 1.211965, 0.194237]
test_list.append(turb_naca0012_1c)
# NACA0012 2c
turb_naca0012_2c = TestCase('turb_naca0012_2c')
turb_naca0012_2c.cfg_dir = "rans_uq/naca0012"
turb_naca0012_2c.cfg_file = "turb_NACA0012_uq_2c.cfg"
turb_naca0012_2c.test_iter = 10
turb_naca0012_2c.test_vals = [-5.484195, 0.969789, 1.310525, 0.231240]
test_list.append(turb_naca0012_2c)
# NACA0012 3c
turb_naca0012_3c = TestCase('turb_naca0012_3c')
turb_naca0012_3c.cfg_dir = "rans_uq/naca0012"
turb_naca0012_3c.cfg_file = "turb_NACA0012_uq_3c.cfg"
turb_naca0012_3c.test_iter = 10
turb_naca0012_3c.test_vals = [-5.586959, 0.932359, 1.535455, 0.315820]
test_list.append(turb_naca0012_3c)
# NACA0012 p1c1
turb_naca0012_p1c1 = TestCase('turb_naca0012_p1c1')
turb_naca0012_p1c1.cfg_dir = "rans_uq/naca0012"
turb_naca0012_p1c1.cfg_file = "turb_NACA0012_uq_p1c1.cfg"
turb_naca0012_p1c1.test_iter = 10
turb_naca0012_p1c1.test_vals = [-5.132081, 1.076462, 1.178093, 0.181595]
test_list.append(turb_naca0012_p1c1)
# NACA0012 p1c2
turb_naca0012_p1c2 = TestCase('turb_naca0012_p1c2')
turb_naca0012_p1c2.cfg_dir = "rans_uq/naca0012"
turb_naca0012_p1c2.cfg_file = "turb_NACA0012_uq_p1c2.cfg"
turb_naca0012_p1c2.test_iter = 10
turb_naca0012_p1c2.test_vals = [-5.556648, 0.945129, 1.240986, 0.205071]
test_list.append(turb_naca0012_p1c2)
######################################
### Harmonic Balance ###
######################################
# Description of the regression test
harmonic_balance = TestCase('harmonic_balance')
harmonic_balance.cfg_dir = "harmonic_balance"
harmonic_balance.cfg_file = "HB.cfg"
harmonic_balance.test_iter = 25
harmonic_balance.test_vals = [-1.589755, 3.922207, 0.006725, 0.099455]
harmonic_balance.new_output = False
test_list.append(harmonic_balance)
# Turbulent pitching NACA 64a010 airfoil
hb_rans_preconditioning = TestCase('hb_rans_preconditioning')
hb_rans_preconditioning.cfg_dir = "harmonic_balance/hb_rans_preconditioning"
hb_rans_preconditioning.cfg_file = "davis.cfg"
hb_rans_preconditioning.test_iter = 25
hb_rans_preconditioning.test_vals = [
-1.902391, -5.950120, 0.007786, 0.128110
]
hb_rans_preconditioning.new_output = False
test_list.append(hb_rans_preconditioning)
######################################
### Moving Wall ###
######################################
# Lid-driven cavity
cavity = TestCase('cavity')
cavity.cfg_dir = "moving_wall/cavity"
cavity.cfg_file = "lam_cavity.cfg"
cavity.test_iter = 25
cavity.test_vals = [-5.627934, -0.164469, 0.051998, 2.547065]
test_list.append(cavity)
# Spinning cylinder
spinning_cylinder = TestCase('spinning_cylinder')
spinning_cylinder.cfg_dir = "moving_wall/spinning_cylinder"
spinning_cylinder.cfg_file = "spinning_cylinder.cfg"
spinning_cylinder.test_iter = 25
spinning_cylinder.test_vals = [-7.996313, -2.601764, 1.510692, 1.493876]
test_list.append(spinning_cylinder)
######################################
### Unsteady ###
######################################
# Square cylinder
square_cylinder = TestCase('square_cylinder')
square_cylinder.cfg_dir = "unsteady/square_cylinder"
square_cylinder.cfg_file = "turb_square.cfg"
square_cylinder.test_iter = 3
square_cylinder.test_vals = [-1.162572, 0.066371, 1.399790, 2.220393]
square_cylinder.unsteady = True
test_list.append(square_cylinder)
# Gust
sine_gust = TestCase('sine_gust')
sine_gust.cfg_dir = "gust"
sine_gust.cfg_file = "inv_gust_NACA0012.cfg"
sine_gust.test_iter = 5
sine_gust.test_vals = [-1.977520, 3.481804, -0.012404, -0.007452]
sine_gust.unsteady = True
test_list.append(sine_gust)
# Aeroelastic
aeroelastic = TestCase('aeroelastic')
aeroelastic.cfg_dir = "aeroelastic"
aeroelastic.cfg_file = "aeroelastic_NACA64A010.cfg"
aeroelastic.test_iter = 2
aeroelastic.test_vals = [0.074525, 0.033127, -0.001650, -0.000127]
aeroelastic.unsteady = True
test_list.append(aeroelastic)
# Delayed Detached Eddy Simulation
ddes_flatplate = TestCase('ddes_flatplate')
ddes_flatplate.cfg_dir = "ddes/flatplate"
ddes_flatplate.cfg_file = "ddes_flatplate.cfg"
ddes_flatplate.test_iter = 10
ddes_flatplate.test_vals = [-2.714758, -5.883004, -0.215005, 0.023783]
ddes_flatplate.unsteady = True
test_list.append(ddes_flatplate)
######################################
### NICFD ###
######################################
# Rarefaction shock wave edge_VW
edge_VW = TestCase('edge_VW')
edge_VW.cfg_dir = "nicf/edge"
edge_VW.cfg_file = "edge_VW.cfg"
edge_VW.test_iter = 100
edge_VW.test_vals = [-5.040283, 1.124491, -0.000009, 0.000000]
test_list.append(edge_VW)
# Rarefaction shock wave edge_PPR
edge_PPR = TestCase('edge_PPR')
edge_PPR.cfg_dir = "nicf/edge"
edge_PPR.cfg_file = "edge_PPR.cfg"
edge_PPR.test_iter = 100
edge_PPR.test_vals = [-5.401640, 0.738165, -0.000035, 0.000000]
test_list.append(edge_PPR)
######################################
### Turbomachinery ###
######################################
# Jones APU Turbocharger
Jones_tc = TestCase('jones_turbocharger')
Jones_tc.cfg_dir = "turbomachinery/APU_turbocharger"
Jones_tc.cfg_file = "Jones.cfg"
Jones_tc.test_iter = 5
Jones_tc.test_vals = [-5.280316, 0.379651, 72.207590, 1.277638]
Jones_tc.new_output = False
test_list.append(Jones_tc)
# Jones APU Turbocharger restart
Jones_tc_rst = TestCase('jones_turbocharger_restart')
Jones_tc_rst.cfg_dir = "turbomachinery/APU_turbocharger"
Jones_tc_rst.cfg_file = "Jones_rst.cfg"
Jones_tc_rst.test_iter = 5
Jones_tc_rst.test_vals = [-4.625330, -1.568896, 33.995140, 10.181610]
Jones_tc_rst.new_output = False
test_list.append(Jones_tc_rst)
# 2D axial stage
axial_stage2D = TestCase('axial_stage2D')
axial_stage2D.cfg_dir = "turbomachinery/axial_stage_2D"
axial_stage2D.cfg_file = "Axial_stage2D.cfg"
axial_stage2D.test_iter = 20
axial_stage2D.test_vals = [-1.933200, 5.379973, 73.357900, 0.925878]
axial_stage2D.new_output = False
test_list.append(axial_stage2D)
# 2D transonic stator
transonic_stator = TestCase('transonic_stator')
transonic_stator.cfg_dir = "turbomachinery/transonic_stator_2D"
transonic_stator.cfg_file = "transonic_stator.cfg"
transonic_stator.test_iter = 20
transonic_stator.test_vals = [-0.562430, 5.828446, 96.436050, 0.062506]
transonic_stator.new_output = False
test_list.append(transonic_stator)
# 2D transonic stator restart
transonic_stator_rst = TestCase('transonic_stator_restart')
transonic_stator_rst.cfg_dir = "turbomachinery/transonic_stator_2D"
transonic_stator_rst.cfg_file = "transonic_stator_rst.cfg"
transonic_stator_rst.test_iter = 20
transonic_stator_rst.test_vals = [-6.621626, -0.614379, 5.002986, 0.002951]
transonic_stator_rst.new_output = False
test_list.append(transonic_stator_rst)
######################################
### Sliding Mesh ###
######################################
# Uniform flow
uniform_flow = TestCase('uniform_flow')
uniform_flow.cfg_dir = "sliding_interface/uniform_flow"
uniform_flow.cfg_file = "uniform_NN.cfg"
uniform_flow.test_iter = 5
uniform_flow.test_vals = [5.000000, 0.000000, -0.188748, -10.631530]
uniform_flow.unsteady = True
uniform_flow.multizone = True
test_list.append(uniform_flow)
# Channel_2D
channel_2D = TestCase('channel_2D')
channel_2D.cfg_dir = "sliding_interface/channel_2D"
channel_2D.cfg_file = "channel_2D_WA.cfg"
channel_2D.test_iter = 2
channel_2D.test_vals = [2.000000, 0.000000, 0.398089, 0.352762, 0.405397]
channel_2D.unsteady = True
channel_2D.multizone = True
test_list.append(channel_2D)
# Channel_3D
channel_3D = TestCase('channel_3D')
channel_3D.cfg_dir = "sliding_interface/channel_3D"
channel_3D.cfg_file = "channel_3D_WA.cfg"
channel_3D.test_iter = 2
channel_3D.test_vals = [2.000000, 0.000000, 0.620151, 0.505157, 0.415249]
channel_3D.unsteady = True
channel_3D.multizone = True
test_list.append(channel_3D)
# Pipe
pipe = TestCase('pipe')
pipe.cfg_dir = "sliding_interface/pipe"
pipe.cfg_file = "pipe_NN.cfg"
pipe.test_iter = 2
pipe.test_vals = [0.150024, 0.491949, 0.677757, 0.963990, 1.006944]
pipe.unsteady = True
pipe.multizone = True
test_list.append(pipe)
# Rotating cylinders
rotating_cylinders = TestCase('rotating_cylinders')
rotating_cylinders.cfg_dir = "sliding_interface/rotating_cylinders"
rotating_cylinders.cfg_file = "rot_cylinders_WA.cfg"
rotating_cylinders.test_iter = 3
rotating_cylinders.test_vals = [
3.000000, 0.000000, 0.777567, 1.134807, 1.224136
]
rotating_cylinders.unsteady = True
rotating_cylinders.multizone = True
test_list.append(rotating_cylinders)
# Supersonic vortex shedding
supersonic_vortex_shedding = TestCase('supersonic_vortex_shedding')
supersonic_vortex_shedding.cfg_dir = "sliding_interface/supersonic_vortex_shedding"
supersonic_vortex_shedding.cfg_file = "sup_vor_shed_WA.cfg"
supersonic_vortex_shedding.test_iter = 5
supersonic_vortex_shedding.test_vals = [
5.000000, 0.000000, 1.216554, 1.639121
]
supersonic_vortex_shedding.unsteady = True
supersonic_vortex_shedding.multizone = True
test_list.append(supersonic_vortex_shedding)
# Bars_SST_2D
bars_SST_2D = TestCase('bars_SST_2D')
bars_SST_2D.cfg_dir = "sliding_interface/bars_SST_2D"
bars_SST_2D.cfg_file = "bars.cfg"
bars_SST_2D.test_iter = 13
bars_SST_2D.test_vals = [13.000000, -0.619179, -1.564701]
bars_SST_2D.multizone = True
test_list.append(bars_SST_2D)
##########################
### FEA - FSI ###
##########################
# Static beam, 3d
statbeam3d = TestCase('statbeam3d')
statbeam3d.cfg_dir = "fea_fsi/StatBeam_3d"
statbeam3d.cfg_file = "configBeam_3d.cfg"
statbeam3d.test_iter = 0
statbeam3d.test_vals = [-2.378370, -1.585252, -2.028505, 6.4359e+04]
test_list.append(statbeam3d)
# Dynamic beam, 2d
dynbeam2d = TestCase('dynbeam2d')
dynbeam2d.cfg_dir = "fea_fsi/DynBeam_2d"
dynbeam2d.cfg_file = "configBeam_2d.cfg"
dynbeam2d.test_iter = 6
dynbeam2d.test_vals = [-3.240015, 2.895057, -0.353146, 66127.000000]
dynbeam2d.unsteady = True
test_list.append(dynbeam2d)
# FSI, 2d
fsi2d = TestCase('fsi2d')
fsi2d.cfg_dir = "fea_fsi/WallChannel_2d"
fsi2d.cfg_file = "configFSI.cfg"
fsi2d.test_iter = 4
fsi2d.test_vals = [4.000000, 0.000000, -3.764089, -4.081119]
fsi2d.multizone = True
fsi2d.unsteady = True
test_list.append(fsi2d)
# FSI, Static, 2D, new mesh solver
stat_fsi = TestCase('stat_fsi')
stat_fsi.cfg_dir = "fea_fsi/stat_fsi"
stat_fsi.cfg_file = "config.cfg"
stat_fsi.test_iter = 7
stat_fsi.test_vals = [-3.242834, -4.866608, 0.000000, 11.000000]
stat_fsi.multizone = True
test_list.append(stat_fsi)
# FSI, Dynamic, 2D, new mesh solver
dyn_fsi = TestCase('dyn_fsi')
dyn_fsi.cfg_dir = "fea_fsi/dyn_fsi"
dyn_fsi.cfg_file = "config.cfg"
dyn_fsi.test_iter = 4
dyn_fsi.test_vals = [-4.379823, -4.005990, 0.000000, 74.000000]
dyn_fsi.multizone = True
dyn_fsi.unsteady = True
test_list.append(dyn_fsi)
# FSI, Static, 2D, new mesh solver, restart
stat_fsi_restart = TestCase('stat_fsi_restart')
stat_fsi_restart.cfg_dir = "fea_fsi/stat_fsi"
stat_fsi_restart.cfg_file = "config_restart.cfg"
stat_fsi_restart.test_iter = 1
stat_fsi_restart.test_vals = [-3.474239, -4.250710, 0.000000, 36.000000]
stat_fsi_restart.multizone = True
test_list.append(stat_fsi_restart)
##############################################
### Method of Manufactured Solutions (MMS) ###
##############################################
# FVM, compressible, laminar N-S
mms_fvm_ns = TestCase('mms_fvm_ns')
mms_fvm_ns.cfg_dir = "mms/fvm_navierstokes"
mms_fvm_ns.cfg_file = "lam_mms_roe.cfg"
mms_fvm_ns.test_iter = 20
mms_fvm_ns.test_vals = [-2.851428, 2.192348, 0.000000, 0.000000]
test_list.append(mms_fvm_ns)
######################################
### RUN TESTS ###
######################################
for test in test_list:
test.su2_exec = "SU2_CFD -t 2"
test.timeout = 600
test.tol = 1e-4
#end
pass_list = [test.run_test() for test in test_list]
# Tests summary
print('==================================================================')
print('Summary of the parallel tests')
print('python version:', sys.version)
for i, test in enumerate(test_list):
if (pass_list[i]):
print(' passed - %s' % test.tag)
else:
print('* FAILED - %s' % test.tag)
if all(pass_list):
sys.exit(0)
else:
sys.exit(1)
