In [1]:
remote_data = False
remote_server_auto = True
case_name = 'wb_coarse2p48'
data_dir='/home/users/p02208/scratch/case2'
#data_host='dstandingford@vis03'
paraview_cmd='mpiexec.hydra /home/users/p02208/rh-6.5/test/zCFD/bin/pvserver'
if not remote_server_auto:
paraview_cmd=None
if not remote_data:
data_host='localhost'
paraview_cmd=None
In [2]:
import sys
sys.path.append(data_dir)
In [3]:
# Validation criteria setup for CRM lift-matched (C_L = 0.5) L3 mesh drag components
validate = True
regression = True
if (validate):
valid = True
valid_lower_alpha = 2.20000-0.05000
valid_upper_alpha = 2.20000+0.05000
valid_lower_cl = 0.50000-0.00500
valid_upper_cl = 0.50000+0.00500
valid_lower_cd = 0.02502-0.00062
valid_upper_cd = 0.02502+0.00062
valid_lower_cdp = 0.01400-0.00050
valid_upper_cdp = 0.01400+0.00050
valid_lower_cdf = 0.01100-0.00075
valid_upper_cdf = 0.01100+0.00075
print 'VALIDATING CRM DPW5 CASE'
if (regression):
print 'REGRESSION CRM DPW5 L3 CASE'
In [4]:
%pylab inline
from paraview.simple import *
paraview.simple._DisableFirstRenderCameraReset()
import pylab as pl
import math
In [5]:
from zutil.post import pvserver_connect
if remote_data:
pvserver_connect(data_host=data_host,data_dir=data_dir,paraview_cmd=paraview_cmd)
In [6]:
from zutil.post import get_case_parameters,print_html_parameters
parameters=get_case_parameters(case_name,data_host=data_host,data_dir=data_dir)
In [7]:
from zutil.post import get_status_dict
status=get_status_dict(case_name,data_host=data_host,data_dir=data_dir)
num_procs = str(status['num processor'])
In [8]:
#alpha = parameters['IC_1']['alpha'] # degrees
reference_area = 594720.0 # inches^2
reference_length = 275.8 # inches, mean chord.
reference_span = 1156.75 # inches
from IPython.display import HTML
HTML(print_html_parameters(parameters))
Out[8]:
In [9]:
import collections
# Names of cases
case_dict = collections.OrderedDict()
case_dict['wb_coarse2p48'] = {'name' : 'wb_coarse2p48',
'case' : 'CASE2A',
'level' : 2,
'alpha' : 2.489,
'wing' : [14,15,16,17,18,19,22,25],
'N' : 120220034,
}
case_dict['wb_medium2p48'] = {'name' : 'wb_medium2p48',
'case' : 'CASE2A',
'level' : 3,
'alpha' : 2.489,
'wing' : [14,15,16,17,18,19,22,25],
'N' : 171479171,
}
case_dict['wb_fine2p49'] = {'name' : 'wb_fine2p49',
'case' : 'CASE2A',
'level' : 4,
'alpha' : 2.50,
'wing' : [14,15,16,17,18,19,22,25],
'N' : 268135684,
}
case_dict['wbnp_medium2p64'] = {'name' : 'wbnp_medium2p64',
'case' : 'CASE2B',
'level' : 3,
'alpha' : 2.64,
'wing' : [41,42,43,44,45,46,47,49,53],
'N' : 176676926,
}
case_dict['wbnp_fine2p64'] = {'name' : 'wbnp_fine2p64',
'case' : 'CASE2B',
'level' : 4,
'alpha' : 2.64,
'wing' : [41,42,43,44,45,46,47,49,53],
'N': 305307926,
}
In [10]:
import zutil
reload(zutil)
import zutil.post
reload(zutil.post)
from zutil.post import cp_profile_wall_from_file
from zutil.post import cf_profile_wall_from_file
def plot_cp_profile(ax,file_root,span_loc,normal,location,data_table, alpha, filter):
force_data = cp_profile_wall_from_file(file_root,
normal,
location,
func=plot_cp_array,
axis=ax,
span_loc=span_loc,
alpha=alpha,
data_table=data_table,
filter=filter)
def plot_cp_array(data_array,pts_array,**kwargs):
ax = kwargs['axis']
span_loc = kwargs['span_loc']
cp_array = data_array.GetPointData()['cp']
chord_array = data_array.GetPointData()['chord']
ax.plot(chord_array, cp_array , 'b.',color='b',label='zCFD SST-2003')
# Save data in data_array
data_table=kwargs['data_table']
for ind in range(0,len(cp_array)):
data_table.append([0,0,0,0,0,0,0,0,0])
#help(pts_array)
data_table[ind][0] = pts_array.GetPoints()[ind][0]
data_table[ind][1] = pts_array.GetPoints()[ind][1]
data_table[ind][2] = pts_array.GetPoints()[ind][2]
data_table[ind][3] = chord_array[ind]
data_table[ind][4] = cp_array[ind]
# Add sectional force integration - assumes closed loop
#p1 = pts_array.GetPoints()[ind]
#ind_next = ind + 1
#if ind_next > len(cp_array):
# ind_next = 0
#p2 = pts_array.GetPoints()[ind_next]
#
#p2 - p1
def plot_cf_profile(ax,file_root,span_loc,normal,location,data_table, alpha):
force_data = cf_profile_wall_from_file(file_root,
normal,
location,
func=plot_cf_array,
axis=ax,
span_loc=span_loc,
alpha=alpha,
data_table=data_table)
def plot_cf_array(data_array,pts_array,**kwargs):
ax = kwargs['axis']
span_loc = kwargs['span_loc']
cf_array = data_array.GetPointData()['frictionforce']
cfmag_array = data_array.GetPointData()['cfmag']
chord_array = data_array.GetPointData()['chord']
ax.plot(chord_array, cf_array , 'b.',color='b',label='zCFD SST-2003')
# Save data in data_array
data_table=kwargs['data_table']
for ind in range(0,len(cf_array)):
data_table[ind][5] = cfmag_array[ind]
data_table[ind][6] = cf_array[ind][0]
data_table[ind][7] = cf_array[ind][1]
data_table[ind][8] = cf_array[ind][2]
In [11]:
# Define wing cuts
cutter=[]
# WING SECTION 1: ETA = 0.1050, CHORD=466.466
# $!RUNMACROFUNCTION "SECTIONALCUTTER" ( 993.728, 121.459, 176.053,0.000,1.000,0.000)
cutter.append({'eta':0.1050,
'chord':466.466,
'position':[993.728, 121.459, 176.053,0.000,1.000,0.000]})
# WING SECTION 2: ETA = 0.1150, CHORD=459.571
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1002.168, 133.026, 176.306,0.000,1.000,0.000)
cutter.append({'eta':0.1150,
'chord':459.571,
'position':[1002.168, 133.026, 176.306,0.000,1.000,0.000]})
# WING SECTION 3: ETA = 0.1250, CHORD=452.687
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1010.656, 144.594, 176.539,0.000,1.000,0.000)
cutter.append({'eta':0.1250,
'chord':452.687,
'position':[1010.656, 144.594, 176.539,0.000,1.000,0.000]})
# WING SECTION 4: ETA = 0.1306, CHORD=448.836
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1015.435, 151.074, 176.659,0.000,1.000,0.000)
cutter.append({'eta':0.1306,
'chord':448.836,
'position':[1015.435, 151.074, 176.659,0.000,1.000,0.000]})
# WING SECTION 5: ETA = 0.2009, CHORD=400.743
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1076.873, 232.444, 177.509,0.000,1.000,0.000)
cutter.append({'eta':0.2009,
'chord':400.743,
'position':[1076.873, 232.444, 177.509,0.000,1.000,0.000]})
# WING SECTION 6: ETA = 0.2828, CHORD=344.991
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1148.974, 327.074, 178.606,0.000,1.000,0.000)
cutter.append({'eta':0.2828,
'chord':344.991,
'position':[1148.974, 327.074, 178.606,0.000,1.000,0.000]})
# WING SECTION 7: ETA = 0.3430, CHORD=304.101
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1202.038, 396.765, 180.222,0.000,1.000,0.000)
cutter.append({'eta':0.3430,
'chord':304.101,
'position':[1202.038, 396.765, 180.222,0.000,1.000,0.000]})
# WING SECTION 8: ETA = 0.3700, CHORD=285.806
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1225.822, 427.998, 181.162,0.000,1.000,0.000)
cutter.append({'eta':0.3700,
'chord':285.806,
'position':[1225.822, 427.998, 181.162,0.000,1.000,0.000]})
# WING SECTION 9: ETA = 0.3971, CHORD=278.111
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1249.711, 459.370, 182.250,0.000,1.000,0.000)
cutter.append({'eta':0.3971,
'chord':278.111,
'position':[1249.711, 459.370, 182.250,0.000,1.000,0.000]})
# WING SECTION 10: ETA = 0.5024, CHORD=248.312
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1342.440, 581.148, 188.658,0.000,1.000,0.000)
cutter.append({'eta':0.5024,
'chord':248.312,
'position':[1342.440, 581.148, 188.658,0.000,1.000,0.000]})
# WING SECTION 11: ETA = 0.6028, CHORD=219.904
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1430.914, 697.333, 198.060,0.000,1.000,0.000)
cutter.append({'eta':0.6028,
'chord':219.904,
'position':[1430.914, 697.333, 198.060,0.000,1.000,0.000]})
# WING SECTION 12: ETA = 0.7268, CHORD=184.844
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1540.091, 840.704, 213.659,0.000,1.000,0.000)
cutter.append({'eta':0.7268,
'chord':184.844,
'position':[1540.091, 840.704, 213.659,0.000,1.000,0.000]})
# WING SECTION 13: ETA = 0.8456, CHORD=151.235
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1644.738, 978.148, 233.317,0.000,1.000,0.000)
cutter.append({'eta':0.8456,
'chord':151.235,
'position':[1644.738, 978.148, 233.317,0.000,1.000,0.000]})
# WING SECTION 14: ETA = 0.9500, CHORD=121.735
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1736.708,1098.926, 253.727,0.000,1.000,0.000)
cutter.append({'eta':0.9500,
'chord':121.735,
'position':[1736.708,1098.926, 253.727,0.000,1.000,0.000]})
# WING SECTION 15: ETA = 0.9700, CHORD=116.095
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1754.313,1122.048, 257.777,0.000,1.000,0.000)
cutter.append({'eta':0.9700,
'chord':116.095,
'position':[1754.313,1122.048, 257.777,0.000,1.000,0.000]})
# WING SECTION 16: ETA = 0.9900, CHORD=110.452
# $!RUNMACROFUNCTION "SECTIONALCUTTER" (1771.927,1145.183, 261.823,0.000,1.000,0.000)
cutter.append({'eta':0.9900,
'chord':110.452,
'position':[1771.927,1145.183, 261.823,0.000,1.000,0.000]})
In [12]:
from zutil.post import get_case_root
from zutil.post import calc_force_wall
from zutil.post import ProgressBar
def plot_cp(case_name, workshop_case, alpha, data_table, filter):
pbar = ProgressBar()
pressure_force, friction_force = calc_force_wall(data_dir+'/'+get_case_root(case_name,num_procs),
[],half_model=True,
alpha=alpha)
C_L = (pressure_force[2] + friction_force[2])/reference_area
C_D_P = pressure_force[0]/reference_area
C_D_F = friction_force[0]/reference_area
C_D = C_D_P + C_D_F
case_dict[case_name]['cl'] = C_L
case_dict[case_name]['cdp'] = C_D_P
case_dict[case_name]['cdf'] = C_D_F
case_dict[case_name]['cd'] = C_D
return
fig = pl.figure(figsize=(20, 5*len(cutter)), dpi=150, facecolor='w', edgecolor='#E48B25')
fig.suptitle('NASA Common Research Model - Drag Prediction Workshop 6 '+workshop_case+' \n'
+ r'$\alpha$=' + ('%.3f ' % alpha)
+ ('$\mathbf{C_L}$=%.4f ' % C_L)
+ ('$\mathbf{C_D}$=%.4f ' % C_D)
+ ('$\mathbf{C_{D(PR)}}$=%.4f ' % C_D_P)
+ ('$\mathbf{C_{D(FR)}}$=%.4f ' % C_D_F),
fontsize=24, fontweight='normal', color = '#5D5858')
plot = 1
pbar += 5
data_array = data_table[case_name]
data_array['cl_tot'] = C_L
for station in cutter:
span_loc = station['eta']
data_array[span_loc] = []
ax = fig.add_subplot(len(cutter)/2,2,plot)
ax.set_title('$\mathbf{C_p}$ span='+str(span_loc*100)+'% \n',
fontsize=20, fontweight='normal', color = '#E48B25')
ax.grid(True)
ax.set_xlabel('$\mathbf{x/c}$', fontsize=24, fontweight='bold', color = '#5D5858')
ax.set_ylabel('$\mathbf{C_p}$', fontsize=24, fontweight='bold', color = '#5D5858')
ax.axis([0.0,1.0,1.0,-1.2])
normal = [station['position'][i] for i in range(3,6)]
location = [station['position'][i] for i in range(0,3)]
plot_cp_profile(ax,data_dir+'/'+get_case_root(case_name,num_procs),
span_loc,
normal,
location,
data_array[span_loc],
alpha,
filter)
"""
for source, colour in sources:
plotlist_x = []
plotlist_y = []
for key, value in dpw5_comparative_data["L3"][source][station]['X/C'].iteritems():
plotlist_x.append(value)
for key, value in dpw5_comparative_data["L3"][source][station]['CP'].iteritems():
plotlist_y.append(value)
ax.plot(plotlist_x, plotlist_y, 'r.', color=colour, label=source)
"""
legend = ax.legend(loc='best', scatterpoints=1, numpoints=1, shadow=False, fontsize=16)
legend.get_frame().set_facecolor('white')
ax.tick_params(axis='x', pad=16)
for tick in ax.xaxis.get_major_ticks():
tick.label.set_fontsize(18)
tick.label.set_fontweight('normal')
tick.label.set_color('#E48B25')
for tick in ax.yaxis.get_major_ticks():
tick.label.set_fontsize(18)
tick.label.set_fontweight('normal')
tick.label.set_color('#E48B25')
plot += 1
pbar+=5
fig.subplots_adjust(hspace=0.3)
fig.savefig('images/DPW6_'+workshop_case+'_cp_profile.png')
pbar.complete()
show()
#from IPython.display import FileLink, display
#display(FileLink('images/DPW6_cp_profile.png'))
def plot_cf(case_name, alpha, data_table):
pbar = ProgressBar()
pressure_force, friction_force = calc_force_wall(data_dir+'/'+get_case_root(case_name,num_procs),
[],half_model=True,
alpha=alpha)
C_L = (pressure_force[2] + friction_force[2])/reference_area
C_D_P = pressure_force[0]/reference_area
C_D_F = friction_force[0]/reference_area
C_D = C_D_P + C_D_F
fig = pl.figure(figsize=(20, 10*len(cutter)), dpi=150, facecolor='w', edgecolor='#E48B25')
fig.suptitle('NASA Common Research Model - Drag Prediction Workshop 6 \n'
+ r'$\alpha$=' + ('%.3f ' % alpha)
+ ('$\mathbf{C_L}$=%.4f ' % C_L)
+ ('$\mathbf{C_D}$=%.4f ' % C_D)
+ ('$\mathbf{C_{D(PR)}}$=%.4f ' % C_D_P)
+ ('$\mathbf{C_{D(FR)}}$=%.4f ' % C_D_F),
fontsize=24, fontweight='normal', color = '#5D5858')
plot = 1
pbar += 5
data_array = data_table[case_name]
for station in cutter:
span_loc = station['eta']
ax = fig.add_subplot(len(cutter)/2,2,plot)
ax.set_title('$\mathbf{C_p}$ span='+str(span_loc*100)+'% \n',
fontsize=20, fontweight='normal', color = '#E48B25')
ax.grid(True)
ax.set_xlabel('$\mathbf{x/c}$', fontsize=24, fontweight='bold', color = '#5D5858')
ax.set_ylabel('$\mathbf{C_f}$', fontsize=24, fontweight='bold', color = '#5D5858')
ax.axis([0.0,1.0,1.0,-1.2])
normal = [station['position'][i] for i in range(3,6)]
location = [station['position'][i] for i in range(0,3)]
plot_cf_profile(ax,data_dir+'/'+get_case_root(case_name,num_procs),
span_loc,
normal,
location,
data_array[span_loc],
alpha)
"""
for source, colour in sources:
plotlist_x = []
plotlist_y = []
for key, value in dpw5_comparative_data["L3"][source][station]['X/C'].iteritems():
plotlist_x.append(value)
for key, value in dpw5_comparative_data["L3"][source][station]['CP'].iteritems():
plotlist_y.append(value)
ax.plot(plotlist_x, plotlist_y, 'r.', color=colour, label=source)
"""
legend = ax.legend(loc='best', scatterpoints=1, numpoints=1, shadow=False, fontsize=16)
legend.get_frame().set_facecolor('white')
ax.tick_params(axis='x', pad=16)
for tick in ax.xaxis.get_major_ticks():
tick.label.set_fontsize(18)
tick.label.set_fontweight('normal')
tick.label.set_color('#E48B25')
for tick in ax.yaxis.get_major_ticks():
tick.label.set_fontsize(18)
tick.label.set_fontweight('normal')
tick.label.set_color('#E48B25')
plot += 1
pbar+=5
fig.subplots_adjust(hspace=0.3)
fig.savefig("images/DPW6_'+case_name+'_cf_profile.png")
pbar.complete()
show()
#from IPython.display import FileLink, display
#display(FileLink('images/DPW6_cf_profile.png'))
In [13]:
data_table = {}
for case in case_dict:
case_name = case_dict[case]['name']
alpha = case_dict[case]['alpha']
data_table[case_name] = {}
workshop_case = case_dict[case]['case'] + '-L'+str(case_dict[case]['level'])
plot_cp(case_name, workshop_case, alpha, data_table, case_dict[case]['wing'])
#plot_cf(case_name, alpha, data_table)
In [29]:
zeno_orange = '#E58B1C'
zeno_grey = '#5D5858'
cl = []
cd = []
N = []
cl_np = []
cd_np = []
N_np = []
for case in case_dict:
case_var = case_dict[case]
if case_var['case'] == 'CASE2A':
cl.append(case_var['cl'])
cd.append(case_var['cd'])
#print math.pow(float(case_var['N']),-2.0/3.0)
N.append(math.pow(float(case_var['N']),-2.0/3.0))
print case_var['case'], case_var['level'], cd[-1]
else:
cl_np.append(case_var['cl'])
cd_np.append(case_var['cd'])
N_np.append(math.pow(float(case_var['N']),-2.0/3.0))
print case_var['case'], case_var['level'], cd_np[-1]
fig = figure(figsize=(22, 10), dpi=150, facecolor='w', edgecolor=zeno_orange)
fig.suptitle(r'CASE 2 Drag Increment',
fontsize=24, fontweight='normal', color = zeno_grey)
ax = fig.add_subplot(1,2,1)
ax.grid(True)
ax.set_xlabel(r'N^(-2/3)', fontsize=24, fontweight='normal', color = zeno_grey)
ax.set_ylabel(r'$\mathbf{C_d}$', fontsize=24, fontweight='normal', color = zeno_grey)
ax.axis([0.0,5e-6,0.02,0.04])
ax.scatter(N,cd,color=zeno_orange, marker="^", s=149,
label='zCFD Wing Body')
ax.scatter(N_np,cd_np,color='green', marker="^", s=149,
label='zCFD Wing Body Pylon Nacelle')
legend = ax.legend(loc='lower right', scatterpoints=1, numpoints=1, shadow=False, fontsize=20)
legend.get_frame().set_facecolor('white')
ax.tick_params(axis='x', pad=16)
for tick in ax.xaxis.get_major_ticks():
tick.label.set_fontsize(18)
tick.label.set_fontweight('normal')
tick.label.set_color(zeno_orange)
for tick in ax.yaxis.get_major_ticks():
tick.label.set_fontsize(18)
tick.label.set_fontweight('normal')
tick.label.set_color(zeno_orange)
ax = fig.add_subplot(1,2,2)
ax.grid(True)
ax.set_xlabel(r'Mesh Level', fontsize=24, fontweight='normal', color = zeno_grey)
ax.set_ylabel(r'$\mathbf{C_d}$ delta', fontsize=24, fontweight='normal', color = zeno_grey)
ax.axis([0,4,0,0.03])
"""
ax.scatter(data[1], data[2], color='green', marker = "o", s=100,
label='Ladson ' + '$\mathbf{Re}$' + ' = 6m (fixed transition)')
ax.scatter(cl, cd, marker="^", s=149, color=zeno_orange,
label='zCFD ' + '$\mathbf{Re}$' + ' = 6m (fully turbulent)')
ax.scatter(cl_comp, cd_comp, marker="x", s=169, color='black', label='CFL3D SST-V 897x257')
"""
legend = ax.legend(loc='lower right', scatterpoints=1, numpoints=1, shadow=False, fontsize=20)
#legend.get_frame().set_facecolor('white')
ax.tick_params(axis='x', pad=16)
for tick in ax.xaxis.get_major_ticks():
tick.label.set_fontsize(18)
tick.label.set_fontweight('normal')
tick.label.set_color(zeno_orange)
for tick in ax.yaxis.get_major_ticks():
tick.label.set_fontsize(18)
tick.label.set_fontweight('normal')
tick.label.set_color(zeno_orange)
fig.subplots_adjust(wspace=0.3)
fig.savefig("images/case2_drag_increment.png")
show()
from IPython.display import FileLink, display
display(FileLink('images/case2_drag_increment.png'))
In [13]:
from string import Template
def write_tecplot(data_table, workshop_case, mesh_level, alpha):
title = 'AllanM-Custom-SST-2003'
name = 'AllanM'
solver = 'zCFD'
algorithm = 'Finite Volume Explicit'
turbulence_model = 'SST-2003'
grid_id = 'Custom'
header_script = Template(r"""#++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++
#
# DPW-VI SECTIONAL CP CUT DATA SUBMITTAL FORM (Version 4 - 22 April 2016)
#
# Due 14 MAY 2016
#
# XXX: First-author participant's last name + specific identifier if submitting
# multiple grid types, soln methods, turb models, etc.
# EXAMPLES: JonesG-CommonMB-SST-1
# JonesG-CommonOverset-SA-1
# JonesG-CommonOverset-SA-2
# JonesG-CommonHex-kw-1
# JonesG-CommonHybrid-ke-1
# JonesG-CommonPrism-SST-1
# JonesG-Custom-SA-1
# etc.
#
# NOMENCLATURE:
# GRID_LEVEL: Level of grid refinement (1-6)
# GRID_SIZE: Number of grid nodes or cells
# ALPHA: Angle of Attack, deg
# CL: Coefficient of Lift (total) (L/(0.5*rho_inf*U_inf^2*A) )
# CD: Coefficient of Drag (total) (D/(0.5*rho_inf*U_inf^2*A) )
# CM: Coefficient of Pitching Moment (total) (M/(0.5*rho_inf*U_inf^2*A*c)) (+ nose-up)
# CD_PR: Surface-Pressure Integrated Drag Coefficient
# CD_SF: Skin-Friction Integrated Drag Coefficient
# CD-CL2/PA: CD_TOT - (CL_TOT*CL_TOT)/(PI*AR)
# *_TOT: Total Configuration Force/Moment
# *_WING: Wing Component Force/Moment
# *_FUS: Fuselage Component Force/Moment
# ETA: Span fraction = y/BO2
#
# X: X coordinate
# Y: Y coordinate
# Z: Z coordinate
# X/C: Chord Fraction = (X - X_LE)/CHORD
# CP: Coefficient of pressure
# CF: Skin-friction coefficient at wall [tauw/(freestream dynamic pressure)]
# CFX,CFY,CFZ: Components of skin-friction coefficient at wall
#
# CUT DEFINITIONS: ETA X_LE Y_LE Z_LE CHORD
# WING SECTION 1: 0.1050 993.728 121.459 176.053 466.466
# WING SECTION 2: 0.1150 1002.168 133.026 176.306 459.571
# WING SECTION 3: 0.1250 1010.656 144.594 176.539 452.687
# WING SECTION 4: 0.1306 1015.435 151.074 176.659 448.836
# WING SECTION 5: 0.2009 1076.873 232.444 177.509 400.743
# WING SECTION 6: 0.2828 1148.974 327.074 178.606 344.991
# WING SECTION 7: 0.3430 1202.038 396.765 180.222 304.101
# WING SECTION 8: 0.3700 1225.822 427.998 181.162 285.806
# WING SECTION 9: 0.3971 1249.711 459.370 182.250 278.111
# WING SECTION 10: 0.5024 1342.440 581.148 188.658 248.312
# WING SECTION 11: 0.6028 1430.914 697.333 198.060 219.904
# WING SECTION 12: 0.7268 1540.091 840.704 213.659 184.844
# WING SECTION 13: 0.8456 1644.738 978.148 233.317 151.235
# WING SECTION 14: 0.9500 1736.708 1098.926 253.727 121.735
# WING SECTION 15: 0.9700 1754.313 1122.048 257.777 116.095
# WING SECTION 16: 0.9900 1771.927 1145.183 261.823 110.452
#
# Tecplot macro: DPW-VI.SectionalCutter_v1.mcr will define cuts
#
# REFERENCE VALUES:
# Planform ref area, A = 594720.00 inches^2
# Mean aerodynamic chord, Cref = 275.80 inches
# Full-span length, B = 2313.50 inches
# Semi-span length, BO2 = 1156.75 inches
# x moment center = 1325.90 inches
# y moment center = 468.75 inches
# z moment center = 177.95 inches
# Aspect Ratio, AR = 9.00
#
# FLOW CONDITIONS:
# Mach Number: 0.85
# Reynolds Number: 5.0 million (based on Cref=275.80)
# Freestream Temp: 100 deg F
#
# NOTES: 1. All numerical data fields can be free-formatted.
# 2. Please use at least 4 decimal places for coordinate values
# 3. Please use at least 6 decimal places for coefficient values
# 4. Only include one grid type, grid size, soln method, turb model, etc per form.
# 5. Fill fields with value of -999 for data that are not available.
#
#++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++
TITLE = "$XXX"
VARIABLES = "X" "Y" "Z" "X/C" "CP" "CF" "CFX" "CFY" "CFZ"
#---------------------------------------------------
# PARTICIPANT, GRID, AND SOLVER INFORMATION
#---------------------------------------------------
DATASETAUXDATA Name = "$Name_of_Participant"
DATASETAUXDATA SubmissionDate = "Date of Submission"
DATASETAUXDATA SolverName = "$Solver_name"
DATASETAUXDATA BasicAlgorithm = "$Algorithm"
DATASETAUXDATA TurbulenceModel = "SST-2003"
DATASETAUXDATA Miscellaneous = "???"
DATASETAUXDATA GridId = "Custom"
DATASETAUXDATA Mach = "0.85"
#-------------------------------------------------------------------------------
#CASE 2A: WING/BODY SINGLE-POINT GRID CONVERGENCE STUDY
# REQUIRED: L2, L3, L4, L5 (COARSE, MEDIUM, FINE, EXTRAFINE) GRIDS
# OPTIONAL: L1, L6 (TINY, SUPERFINE) GRIDS
# Separate File for each grid level
#-------------------------------------------------------------------------------
#CASE 2B: WING/BODY/NACELLE/PYLON SINGLE-POINT GRID CONVERGENCE STUDY
# REQUIRED: L2, L3, L4, L5 (COARSE, MEDIUM, FINE, EXTRAFINE) GRIDS
# OPTIONAL: L1, L6 (TINY, SUPERFINE) GRIDS
# Separate File for each grid level
#-------------------------------------------------------------------------------
#CASE 3: WING-BODY STATIC AEROELASTIC STUDY (L3, MEDIUM GRID)
# REQUIRED: ALPHA = 2.50, 2.75, 3.00, 3.25, 3.50, 3.75, 4.00
# OPTIONAL: ADDITIONAL ANGLES
# Separate File for each angle of attack
#-------------------------------------------------------------------------------
#CASE 4: WING-BODY SOLUTION ADAPTIVE GRID STUDY
# OPTIONAL: ALPHA = 2.50, 2.75, 3.00, 3.25, 3.50, 3.75, 4.00
# OPTIONAL: ADDITIONAL ANGLES
# Separate File for each angle of attack
#-------------------------------------------------------------------------------
#CASE 5: WING-BODY COUPLED AEROELASTIC STUDY (L3, MEDIUM GRID
# OPTIONAL: ALPHA = 2.50, 2.75, 3.00, 3.25, 3.50, 3.75, 4.00
# OPTIONAL: ADDITIONAL ANGLES
# Separate File for each angle of attack
#-------------------------------------------------------------------------------
#CASE 6: WING-BODY PATTICIPANT GENERATED GRID STUDY
# OPTIONAL: ALPHA = 2.50, 2.75, 3.00, 3.25, 3.50, 3.75, 4.00
# OPTIONAL: ADDITIONAL ANGLES
# Separate File for each angle of attack
#-------------------------------------------------------------------------------""")
script_str = header_script.substitute({'XXX':title,
'Name_of_Participant':name,
'Solver_name':solver,
'Algorithm':algorithm,
})
data_script = Template("""
ZONE T="GRIDLEVEL=L$level ALPHA=$alpha - WING SECTION $section"
AUXDATA CFDCASE = "$CASE"
AUXDATA ID = "id - to be specified by the committee upon receipt"
AUXDATA Name = "$Name_of_Participant"
AUXDATA SolverName = "$Solver_name"
AUXDATA TurbulenceModel = "SST-2003"
AUXDATA GridId = "Custom"
AUXDATA GridLevel = "$level"
AUXDATA ALPHA = "$alpha"
AUXDATA CLTOTAL = "$CLTOTAL"
AUXDATA ETA = "0.105"
""")
i = 1
for cut in cutter:
eta = cut['eta']
cl_tot = data_table['cl_tot']
data_str = data_script.substitute({'level':mesh_level,
'alpha':alpha,
'section':i,
'CASE':workshop_case,
'Name_of_Participant':name,
'Solver_name':solver,
'CLTOTAL':cl_tot,
})
i += 1
script_str += data_str
for p in data_table[eta]:
for c in range(0,3):
script_str += ' {: .4f} '.format(p[c])
for c in range(3,len(p)):
script_str += ' {: .6f} '.format(p[c])
script_str += '\n'
#print eta
#print data_table[eta][0]
#print script_str
with open(workshop_case+'-L'+str(mesh_level)+"-SectionalCuts.dat", "w") as text_file:
text_file.write(script_str)
for case in cases:
case_name = case[0]
alpha = case[1]
workshop_case = case[2]
mesh_level = case[3]
data_table[case_name]
write_tecplot(data_table[case_name], workshop_case, mesh_level, alpha)
In [12]:
from zutil.post import residual_plot, get_case_report
residual_plot(get_case_report(case_name))
show()
In [13]:
if (validate):
valid = (validate_data('alpha', alpha, valid_lower_alpha, valid_upper_alpha)
and validate_data('C_L', C_L, valid_lower_cl, valid_upper_cl)
and validate_data('C_D', C_D, valid_lower_cd, valid_upper_cd)
and validate_data('C_D_P', C_D_P, valid_lower_cdp, valid_upper_cdp)
and validate_data('C_D_F', C_D_F, valid_lower_cdf, valid_upper_cdf))
if (valid):
print 'VALIDATION = PASS :-)'
else:
print 'VALIDATION = FAIL :-('
In [14]:
if (regression):
import pandas as pd
pd.options.display.float_format = '{:,.6f}'.format
print 'REGRESSION DATA'
regress = {'version' : ['v0.0' , '30k' , 'CURRENT'],
'alpha' : [2.217000, 2.217000, alpha],
'C_L' : [0.497464, 0.498132, C_L],
'C_D' : [0.024460, 0.024495, C_D],
'C_D_P' : [0.014094, 0.014099, C_D_P],
'C_D_F' : [0.010366, 0.010396, C_D_F]}
regression_table = pd.DataFrame(regress, columns=['version','alpha','C_L','C_D','C_D_P','C_D_F'])
print regression_table
In [15]:
if remote_data:
print 'Disconnecting from remote paraview server connection'
Disconnect()