def run_mesh_deformation(tixi, wkdir):
"""Function to run all the configuration files with SU2_DEF.
Function 'run_mesh_deformation' will check in all config file directory and run
SU2_DEF for each config file in order.
Args:
tixi (handles): TIXI Handle
wkdir (str): Path to the working directory
"""
log.info('All mesh deromation will be preformed.')
mesh_dir = os.path.join(wkdir, 'MESH')
if not os.path.exists(mesh_dir):
raise OSError('The MESH directory : ' + mesh_dir + 'does not exit!')
os.chdir(mesh_dir)
su2_def_mesh_list = []
ted_dir_list = [dir for dir in os.listdir(mesh_dir) if '_TED_' in dir]
# Iterate in all TED directory
for dir in sorted(ted_dir_list):
ted_dir = os.path.join(mesh_dir, dir)
os.chdir(ted_dir)
cfg_file_list = [
file for file in os.listdir(ted_dir) if 'Config' in file
]
# Run all the config file in the directory with SU2_DEF, in alphabetical
# order to respect the order of execution (DEF,ROT_,ROT_sym)
for cfg_file in sorted(cfg_file_list):
if os.path.isfile(cfg_file):
su2f.run_soft('SU2_DEF', cfg_file, ted_dir)
else:
raise ValueError("Not correct configuration file to run!")
tmp_su2_mesh_list = [
file for file in os.listdir(ted_dir) if '.su2' in file
]
# Copy in the completly deform mesh in the MESH directory
for su2_mesh in tmp_su2_mesh_list:
if not su2_mesh.startswith('_'):
shutil.copyfile(su2_mesh, os.path.join('..', su2_mesh))
log.info(su2_mesh + ' mesh has been copied in the MESH dir.')
su2_def_mesh_list.append(su2_mesh)
# Remove all SU2 mesh from the config folder (to save space)
os.remove(su2_mesh)
log.info(su2_mesh + ' mesh has been deleted from the temp mesh.')
# Add the list of available SU2 deformed mesh in the CPACS file
su2_def_mesh_xpath = SU2_XPATH + '/availableDeformedMesh'
cpsf.add_string_vector(tixi, su2_def_mesh_xpath, su2_def_mesh_list)
def test_add_sting_vector():
""" Test the function 'add_sting_vector'"""
tixi = cpsf.open_tixi(CPACS_IN_PATH)
xpath = '/cpacs/toolspecific/CEASIOMpy/testVector/'
# Add a new vector
string_vector = ['aaa', 'bbb', 'ccc']
cpsf.add_string_vector(tixi, xpath, string_vector)
added_sting_vector_str = tixi.getTextElement(xpath)
added_sting_vector = added_sting_vector_str.split(';')
added_sting_vector = [str(elem) for elem in added_sting_vector]
assert added_sting_vector == string_vector
# Update a vector
string_vector = ['abc', '123', 'test-01']
cpsf.add_string_vector(tixi, xpath, string_vector)
added_sting_vector_str = tixi.getTextElement(xpath)
added_sting_vector = added_sting_vector_str.split(';')
added_sting_vector = [str(elem) for elem in added_sting_vector]
assert added_sting_vector == string_vector
def test_get_string_vector():
""" Test the function 'get_string_vector'"""
tixi = cpsf.open_tixi(CPACS_IN_PATH)
xpath = '/cpacs/toolspecific/CEASIOMpy/testVector'
# Add a new vector
string_vector = ['aaa', 'zzz']
cpsf.add_string_vector(tixi, xpath, string_vector)
# Get a string vector
string_vector_get = cpsf.get_string_vector(tixi, xpath)
assert string_vector_get == string_vector
# Raise an error when the XPath is wrong
wrong_xpath = '/cpacs/toolspecific/CEASIOMpy/testVectorWrong'
with pytest.raises(ValueError):
vector = cpsf.get_string_vector(tixi, wrong_xpath)
# Raise an error when no value at XPath
no_value_xpath = '/cpacs/toolspecific/CEASIOMpy'
with pytest.raises(ValueError):
vector = cpsf.get_string_vector(tixi, no_value_xpath)
def add_skin_friction(cpacs_path, cpacs_out_path):
""" Function to add the skin frinction drag coeffienct to aerodynamic coefficients
Function 'add_skin_friction' add the skin friction drag 'cd0' to the
SU2 and pyTornado aeroMap, if their UID is not geven, it will add skin
friction to all aeroMap. For each aeroMap it creates a new aeroMap where
the skin friction drag coeffienct is added with the correct projcetions.
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str): Path to CPACS output file
"""
tixi = cpsf.open_tixi(cpacs_path)
tigl = cpsf.open_tigl(tixi)
wing_area_max, wing_span_max = get_largest_wing_dim(tixi, tigl)
analyses_xpath = '/cpacs/toolspecific/CEASIOMpy/geometry/analysis'
# Requiered input data from CPACS
wetted_area = cpsf.get_value(tixi, analyses_xpath + '/wettedArea')
# Wing area/span, default values will be calated if no value found in the CPACS file
wing_area_xpath = analyses_xpath + '/wingArea'
wing_area = cpsf.get_value_or_default(tixi, wing_area_xpath, wing_area_max)
wing_span_xpath = analyses_xpath + '/wingSpan'
wing_span = cpsf.get_value_or_default(tixi, wing_span_xpath, wing_span_max)
aeromap_uid_list = []
# Try to get aeroMapToCalculate
aeroMap_to_clculate_xpath = SF_XPATH + '/aeroMapToCalculate'
if tixi.checkElement(aeroMap_to_clculate_xpath):
aeromap_uid_list = cpsf.get_string_vector(tixi,
aeroMap_to_clculate_xpath)
else:
aeromap_uid_list = []
# If no aeroMap in aeroMapToCalculate, get all existing aeroMap
if len(aeromap_uid_list) == 0:
try:
aeromap_uid_list = apmf.get_aeromap_uid_list(tixi)
except:
raise ValueError(
'No aeroMap has been found in this CPACS file, skin friction cannot be added!'
)
# Get unique aeroMap list
aeromap_uid_list = list(set(aeromap_uid_list))
new_aeromap_uid_list = []
# Add skin friction to all listed aeroMap
for aeromap_uid in aeromap_uid_list:
log.info('adding skin friction coefficients to: ' + aeromap_uid)
# Get orignial aeroPerformanceMap
AeroCoef = apmf.get_aeromap(tixi, aeromap_uid)
AeroCoef.complete_with_zeros()
# Create new aeroCoefficient object to store coef with added skin friction
AeroCoefSF = apmf.AeroCoefficient()
AeroCoefSF.alt = AeroCoef.alt
AeroCoefSF.mach = AeroCoef.mach
AeroCoefSF.aoa = AeroCoef.aoa
AeroCoefSF.aos = AeroCoef.aos
# Iterate over all cases
case_count = AeroCoef.get_count()
for case in range(case_count):
# Get parameters for this case
alt = AeroCoef.alt[case]
mach = AeroCoef.mach[case]
aoa = AeroCoef.aoa[case]
aos = AeroCoef.aos[case]
# Calculate Cd0 for this case
cd0 = estimate_skin_friction_coef(wetted_area,wing_area,wing_span, \
mach,alt)
# Projection of cd0 on cl, cd and cs axis
#TODO: Should Cd0 be projected or not???
aoa_rad = math.radians(aoa)
aos_rad = math.radians(aos)
cd0_cl = cd0 * math.sin(aoa_rad)
cd0_cd = cd0 * math.cos(aoa_rad) * math.cos(aos_rad)
cd0_cs = cd0 * math.sin(aos_rad)
# Update aerodynamic coefficients
cl = AeroCoef.cl[case] + cd0_cl
cd = AeroCoef.cd[case] + cd0_cd
cs = AeroCoef.cs[case] + cd0_cs
# Shoud we change something? e.i. if a force is not apply at aero center...?
if len(AeroCoef.cml):
cml = AeroCoef.cml[case]
else:
cml = 0.0 # Shoud be change, just to test pyTornado
if len(AeroCoef.cmd):
cmd = AeroCoef.cmd[case]
else:
cmd = 0.0
if len(AeroCoef.cms):
cms = AeroCoef.cms[case]
else:
cms = 0.0
# Add new coefficients into the aeroCoefficient object
AeroCoefSF.add_coefficients(cl, cd, cs, cml, cmd, cms)
# Create new aeroMap UID
aeromap_sf_uid = aeromap_uid + '_SkinFriction'
new_aeromap_uid_list.append(aeromap_sf_uid)
# Create new description
description_xpath = tixi.uIDGetXPath(aeromap_uid) + '/description'
sf_description = cpsf.get_value(
tixi,
description_xpath) + ' Skin friction has been add to this AeroMap.'
apmf.create_empty_aeromap(tixi, aeromap_sf_uid, sf_description)
# Save aeroCoefficient object Coef in the CPACS file
apmf.save_parameters(tixi, aeromap_sf_uid, AeroCoefSF)
apmf.save_coefficients(tixi, aeromap_sf_uid, AeroCoefSF)
# Get aeroMap list to plot
plot_xpath = '/cpacs/toolspecific/CEASIOMpy/aerodynamics/plotAeroCoefficient'
aeromap_to_plot_xpath = plot_xpath + '/aeroMapToPlot'
if tixi.checkElement(aeromap_to_plot_xpath):
aeromap_uid_list = cpsf.get_string_vector(tixi, aeromap_to_plot_xpath)
new_aeromap_to_plot = aeromap_uid_list + new_aeromap_uid_list
new_aeromap_to_plot = list(set(new_aeromap_to_plot))
cpsf.add_string_vector(tixi, aeromap_to_plot_xpath,
new_aeromap_to_plot)
else:
cpsf.create_branch(tixi, aeromap_to_plot_xpath)
cpsf.add_string_vector(tixi, aeromap_to_plot_xpath,
new_aeromap_uid_list)
log.info('AeroMap "' + aeromap_uid + '" has been added to the CPACS file')
cpsf.close_tixi(tixi, cpacs_out_path)
def plot_aero_coef(cpacs_path, cpacs_out_path):
"""Plot Aero coefficients from the chosen aeroMap in the CPACS file
Function 'plot_aero_coef' can plot one or several aeromap from the CPACS
file according to some user option, these option will be shown in the the
SettingGUI or default values will be used.
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str):Path to CPACS output file
"""
# Open TIXI handle
tixi = cpsf.open_tixi(cpacs_path)
aircraft_name = cpsf.aircraft_name(tixi)
# Get aeroMap list to plot
aeromap_to_plot_xpath = PLOT_XPATH + '/aeroMapToPlot'
aeromap_uid_list = []
# Option to select aeromap manualy
manual_selct = cpsf.get_value_or_default(tixi,
PLOT_XPATH + '/manualSelection',
False)
if manual_selct:
aeromap_uid_list = call_select_aeromap(tixi)
cpsf.create_branch(tixi, aeromap_to_plot_xpath)
cpsf.add_string_vector(tixi, aeromap_to_plot_xpath, aeromap_uid_list)
else:
try:
aeromap_uid_list = cpsf.get_string_vector(tixi,
aeromap_to_plot_xpath)
except:
# If aeroMapToPlot is not define, select manualy anyway
aeromap_uid_list = call_select_aeromap(tixi)
cpsf.create_branch(tixi, aeromap_to_plot_xpath)
cpsf.add_string_vector(tixi, aeromap_to_plot_xpath,
aeromap_uid_list)
# Create DataFrame from aeromap(s)
aeromap_df_list = []
for aeromap_uid in aeromap_uid_list:
aeromap_df = apmf.get_datafram_aeromap(tixi, aeromap_uid)
aeromap_df['uid'] = aeromap_uid
aeromap_df_list.append(aeromap_df)
aeromap = pd.concat(aeromap_df_list, ignore_index=True)
if len(aeromap_uid_list) > 1:
uid_crit = None
else:
uid_crit = aeromap_uid_list[0]
# Default options
title = aircraft_name
criterion = pd.Series([True] * len(aeromap.index))
groupby_list = ['uid', 'mach', 'alt', 'aos']
# Get criterion from CPACS
crit_xpath = PLOT_XPATH + '/criterion'
alt_crit = cpsf.get_value_or_default(tixi, crit_xpath + '/alt', 'None')
mach_crit = cpsf.get_value_or_default(tixi, crit_xpath + '/mach', 'None')
aos_crit = cpsf.get_value_or_default(tixi, crit_xpath + '/aos', 'None')
cpsf.close_tixi(tixi, cpacs_out_path)
# Modify criterion and title according to user option
if len(aeromap['alt'].unique()) == 1:
title += ' - Alt = ' + str(aeromap['alt'].loc[0])
groupby_list.remove('alt')
elif alt_crit not in NONE_LIST:
criterion = criterion & (aeromap.alt == alt_crit)
title += ' - Alt = ' + str(alt_crit)
groupby_list.remove('alt')
if len(aeromap['mach'].unique()) == 1:
title += ' - Mach = ' + str(aeromap['mach'].loc[0])
groupby_list.remove('mach')
elif mach_crit not in NONE_LIST:
criterion = criterion & (aeromap.mach == mach_crit)
title += ' - Mach = ' + str(mach_crit)
groupby_list.remove('mach')
if len(aeromap['aos'].unique()) == 1:
title += ' - AoS = ' + str(aeromap['aos'].loc[0])
groupby_list.remove('aos')
elif aos_crit not in NONE_LIST:
criterion = criterion & (aeromap.aos == aos_crit)
title += ' - AoS = ' + str(aos_crit)
groupby_list.remove('aos')
if uid_crit is not None and len(groupby_list) > 1:
criterion = criterion & (aeromap.uid == uid_crit)
title += ' - ' + uid_crit
groupby_list.remove('uid')
# Plot settings
fig, axs = plt.subplots(2, 3)
fig.suptitle(title, fontsize=14)
fig.set_figheight(8)
fig.set_figwidth(15)
fig.subplots_adjust(left=0.06)
axs[0, 1].axhline(y=0.0, color='k', linestyle='-') # Line at Cm=0
# Plot aerodynamic coerfficients
for value, grp in aeromap.loc[criterion].groupby(groupby_list):
legend = write_legend(groupby_list, value)
axs[0, 0].plot(grp['aoa'], grp['cl'], 'x-', label=legend)
axs[1, 0].plot(grp['aoa'], grp['cd'], 'x-')
axs[0, 1].plot(grp['aoa'], grp['cms'], 'x-')
axs[1, 1].plot(grp['aoa'], grp['cl'] / grp['cd'], 'x-')
axs[0, 2].plot(grp['cd'], grp['cl'], 'x-')
axs[1, 2].plot(grp['cl'], grp['cl'] / grp['cd'], 'x-')
# Set subplot options
subplot_options(axs[0, 0], 'CL', 'AoA')
subplot_options(axs[1, 0], 'CD', 'AoA')
subplot_options(axs[0, 1], 'Cm', 'AoA')
subplot_options(axs[1, 1], 'CL/CD', 'AoA')
subplot_options(axs[0, 2], 'CL', 'CD')
subplot_options(axs[1, 2], 'CL/CD', 'CL')
fig.legend(loc='upper right')
plt.show()
def aeromap_case_gen(modules):
"""
Generate a CSV file containing a dataset generated with aeromap parameters
only.
Args:
modules (lst) : list of modules to execute.
Returns:
file (str) : Path to CSV file.
"""
file = MODULE_DIR + '/Aeromap_generated.csv'
infile = mi.get_toolinput_file_path('PredictiveTool')
outfile = mi.get_tooloutput_file_path('PredictiveTool')
tixi = cpsf.open_tixi(infile)
# Inputs
alt = [0, 0]
mach = [0.5, 0.5]
aoa = [-10, 10]
aos = [0, 0]
nt = 100
bounds = np.array([alt, mach, aoa, aos])
# Sort criterion : ‘center’, ‘maximin’, ‘centermaximin’, ‘correlation’
crit = 'corr'
# Generate sample points, LHS or FullFactorial
sampling = smp.LHS(xlimits=bounds, criterion=crit)
xd = sampling(nt)
xd = xd.transpose()
# Delete the other aeromaps... maybe conserve them ?
for uid in apmf.get_aeromap_uid_list(tixi):
apmf.delete_aeromap(tixi, uid)
# Create new aeromap
aeromap_uid = 'DoE_Aeromap'
am_xpath = tls.get_aeromap_path(modules)
apmf.create_empty_aeromap(tixi, aeromap_uid)
cpsf.add_string_vector(tixi, am_xpath + '/aeroMapUID', [aeromap_uid])
# Add parameters to aeromap
Param = apmf.AeroCoefficient()
for i in range(0, xd.shape[1]):
Param.add_param_point(xd[0][i], xd[1][i], xd[2][i], xd[3][i])
apmf.save_parameters(tixi, aeromap_uid, Param)
cpsf.close_tixi(tixi, infile)
wkf.run_subworkflow(modules, cpacs_path_in=infile, cpacs_path_out=outfile)
# Get Aerocoefficient
tixi = cpsf.open_tixi(outfile)
am_xpath = tls.get_aeromap_path(modules)
aeromap_uid = cpsf.get_value(tixi, am_xpath + '/aeroMapUID')
AeroCoefficient = apmf.get_aeromap(tixi, aeromap_uid)
cpsf.close_tixi(tixi, outfile)
dct = AeroCoefficient.to_dict()
# Write to CSV
df = pd.DataFrame(dct)
df = df.transpose()
var_type = [
'obj' if i in objectives else
'des' if i in ['alt', 'mach', 'aoa', 'aos'] else 'const'
for i in df.index
]
df.insert(0, 'type', var_type)
df.to_csv(file, index=True)
return file
def plot_aero_coef(cpacs_path, cpacs_out_path):
"""Function to plot available aerodynamic coefficients from aeroMap.
Function 'plot_aero_coef' plot aerodynamic coefficients (CL,CD,Cm) of the
aeroMap selected in the CPACS file or if not define, ask the user to select
them.
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str):Path to CPACS output file
"""
# Open TIXI handle
tixi = cpsf.open_tixi(cpacs_path)
# Prepare subplots
figure_1 = plt.figure(figsize=(9, 9))
subplot1 = figure_1.add_subplot(221)
subplot2 = figure_1.add_subplot(222)
subplot3 = figure_1.add_subplot(223)
subplot4 = figure_1.add_subplot(224)
LINE_STYLE = ['bo-', 'ro-', 'go-', 'co-', 'mo-', 'ko-', 'yo-']
# Get aeroMap list to plot
aeromap_to_plot_xpath = PLOT_XPATH + '/aeroMapToPlot'
aeromap_uid_list = []
try:
aeromap_uid_list = cpsf.get_string_vector(tixi, aeromap_to_plot_xpath)
except:
# If aeroMapToPlot is not define, open GUI to select which ones shoud be
aeromap_uid_list = call_select_aeromap(tixi)
cpsf.create_branch(tixi, aeromap_to_plot_xpath)
cpsf.add_string_vector(tixi, aeromap_to_plot_xpath, aeromap_uid_list)
for i, aeromap_uid in enumerate(aeromap_uid_list):
log.info('"' + aeromap_uid + '" will be added to the plot.')
# Get aeroMap to plot and replace missing results with zeros
AeroCoef = apmf.get_aeromap(tixi, aeromap_uid)
AeroCoef.complete_with_zeros()
AeroCoef.print_coef_list()
# Subplot1
x1 = AeroCoef.aoa
y1 = AeroCoef.cl
subplot1.plot(x1, y1, LINE_STYLE[i])
# Subplot2
x2 = AeroCoef.aoa
y2 = AeroCoef.cms
subplot2.plot(x2, y2, LINE_STYLE[i])
# Subplot3
x3 = AeroCoef.aoa
y3 = AeroCoef.cd
subplot3.plot(x3, y3, LINE_STYLE[i])
# Subplot4
x4 = AeroCoef.aoa
if any(AeroCoef.cd) == 0.0:
cl_cd = [0] * len(AeroCoef.aoa)
else:
cl_cd = res = [cl / cd for cl, cd in zip(AeroCoef.cl, AeroCoef.cd)]
y4 = cl_cd
subplot4.plot(x4, y4, LINE_STYLE[i])
# Labels
subplot1.set_xlabel('Angle of attack')
subplot1.set_ylabel('Lift coefficient')
subplot2.set_xlabel('Angle of attack')
subplot2.set_ylabel('Moment coefficient')
subplot3.set_xlabel('Angle of attack')
subplot3.set_ylabel('Drag coefficient')
subplot4.set_xlabel('Angle of attack')
subplot4.set_ylabel('Efficiency CL/CD')
# Legend
figure_1.legend(aeromap_uid_list)
# Grid
subplot1.grid()
subplot2.grid()
subplot3.grid()
subplot4.grid()
cpsf.close_tixi(tixi, cpacs_out_path)
plt.show()