def aeromap_calculation(sm, tixi):
"""Make a prediction using only the aeromap entries.
By using only the aeromap functions this module is way faster to execute. Only
works with the aeromap as the other values of the CPACs are not vectors and
have to be evaluated with a different CPACS every time.
Args:
sm (Surrogate model object): Surrogate used to predict the function output.
tixi (Tixi handle): Handle of the current CPACS.
Returns:
None.
"""
tigl = cpsf.open_tigl(tixi)
aircraft = cpud.get_aircraft(tigl)
wings = aircraft.get_wings()
fuselage = aircraft.get_fuselages().get_fuselage(1)
aeromap_uid = apmf.get_current_aeromap_uid(tixi, 'SMUse')
log.info('Using aeromap :'+aeromap_uid)
Coef = apmf.get_aeromap(tixi, aeromap_uid)
inputs = np.array([Coef.alt, Coef.mach, Coef.aoa, Coef.aos]).T
outputs = sm.predict_values(inputs)
# Re-initiates the values of the results to write the new ones
Coef.cl = []
Coef.cd = []
Coef.cs = []
Coef.cml = []
Coef.cmd = []
Coef.cms = []
for i in range(outputs.shape[0]):
Coef.add_coefficients(outputs[i, 0], outputs[i, 1], outputs[i, 2],
outputs[i, 3], outputs[i, 4], outputs[i, 5])
Coef.print_coef_list()
apmf.save_coefficients(tixi, aeromap_uid, Coef)
tigl.close()
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 get_su2_results(cpacs_path, cpacs_out_path, wkdir):
""" Function to write SU2 results in a CPACS file.
Function 'get_su2_results' get available results from the latest SU2
calculation and put it at the correct place in the CPACS file.
'/cpacs/vehicles/aircraft/model/analyses/aeroPerformance/aerpMap[n]/aeroPerformanceMap'
Args:
cpacs_path (str): Path to input CPACS file
cpacs_out_path (str): Path to output CPACS file
wkdir (str): Path to the working directory
"""
tixi = cpsf.open_tixi(cpacs_path)
# TODO Check and reactivate that
# save_timestamp(tixi,SU2_XPATH) <-- ceaf.replace by get get_execution_date()
if not os.path.exists(wkdir):
raise OSError('The working directory : ' + wkdir + 'does not exit!')
os.chdir(wkdir)
dir_list = os.listdir(wkdir)
# Get and save Wetted area
wetted_area = get_wetted_area(wkdir)
wetted_area_xpath = '/cpacs/toolspecific/CEASIOMpy/geometry/analysis/wettedArea'
cpsf.create_branch(tixi, wetted_area_xpath)
tixi.updateDoubleElement(wetted_area_xpath, wetted_area, '%g')
# Get and save CL/CD ratio
fixed_cl_xpath = SU2_XPATH + '/fixedCL'
fixed_cl = cpsf.get_value_or_default(tixi, fixed_cl_xpath, 'NO')
# TODO
# if fixed_cl == 'YES':
# find force_file_name = 'forces_breakdown.dat'
# cl_cd = get_efficiency(force_path)
# lDRatio_xpath = '/cpacs/toolspecific/CEASIOMpy/ranges/lDRatio' # TODO: probalby change xpath and name
# cpsf.create_branch(tixi, lDRatio_xpath)
# tixi.updateDoubleElement(lDRatio_xpath,cl_cd,'%g')
# Save aeroPerformanceMap
su2_aeromap_xpath = SU2_XPATH + '/aeroMapUID'
aeromap_uid = cpsf.get_value(tixi, su2_aeromap_xpath)
# Check if loads shoud be extracted
check_extract_loads_xpath = SU2_XPATH + '/results/extractLoads'
check_extract_loads = cpsf.get_value_or_default(tixi,
check_extract_loads_xpath,
False)
# Create an oject to store the aerodynamic coefficients
apmf.check_aeromap(tixi, aeromap_uid)
# TODO: create a function to earase previous results...
Coef2 = apmf.get_aeromap(tixi, aeromap_uid)
Coef = apmf.AeroCoefficient()
Coef.alt = Coef2.alt
Coef.mach = Coef2.mach
Coef.aoa = Coef2.aoa
Coef.aos = Coef2.aos
case_dir_list = [dir for dir in dir_list if 'Case' in dir]
for config_dir in sorted(case_dir_list):
if os.path.isdir(config_dir):
os.chdir(config_dir)
force_file_name = 'forces_breakdown.dat'
if not os.path.isfile(force_file_name):
raise OSError('No result force file have been found!')
# Read result file
with open(force_file_name) as f:
for line in f.readlines():
if 'Total CL:' in line:
cl = float(line.split(':')[1].split('|')[0])
if 'Total CD:' in line:
cd = float(line.split(':')[1].split('|')[0])
if 'Total CSF:' in line:
cs = float(line.split(':')[1].split('|')[0])
# TODO: Check which axis name corespond to waht: cml, cmd, cms
if 'Total CMx:' in line:
cmd = float(line.split(':')[1].split('|')[0])
if 'Total CMy:' in line:
cms = float(line.split(':')[1].split('|')[0])
if 'Total CMz:' in line:
cml = float(line.split(':')[1].split('|')[0])
if ('Free-stream velocity' in line and 'm/s' in line):
velocity = float(line.split(' ')[7])
# Damping derivatives
rotation_rate_xpath = SU2_XPATH + '/options/rotationRate'
rotation_rate = cpsf.get_value_or_default(tixi,
rotation_rate_xpath, 1.0)
ref_xpath = '/cpacs/vehicles/aircraft/model/reference'
ref_len = cpsf.get_value(tixi, ref_xpath + '/length')
adim_rot_rate = rotation_rate * ref_len / velocity
if '_dp' in config_dir:
dcl = (cl - Coef.cl[-1]) / adim_rot_rate
dcd = (cd - Coef.cd[-1]) / adim_rot_rate
dcs = (cs - Coef.cs[-1]) / adim_rot_rate
dcml = (cml - Coef.cml[-1]) / adim_rot_rate
dcmd = (cmd - Coef.cmd[-1]) / adim_rot_rate
dcms = (cms - Coef.cms[-1]) / adim_rot_rate
Coef.damping_derivatives.add_damping_der_coef(
dcl, dcd, dcs, dcml, dcmd, dcms, '_dp')
elif '_dq' in config_dir:
dcl = (cl - Coef.cl[-1]) / adim_rot_rate
dcd = (cd - Coef.cd[-1]) / adim_rot_rate
dcs = (cs - Coef.cs[-1]) / adim_rot_rate
dcml = (cml - Coef.cml[-1]) / adim_rot_rate
dcmd = (cmd - Coef.cmd[-1]) / adim_rot_rate
dcms = (cms - Coef.cms[-1]) / adim_rot_rate
Coef.damping_derivatives.add_damping_der_coef(
dcl, dcd, dcs, dcml, dcmd, dcms, '_dq')
elif '_dr' in config_dir:
dcl = (cl - Coef.cl[-1]) / adim_rot_rate
dcd = (cd - Coef.cd[-1]) / adim_rot_rate
dcs = (cs - Coef.cs[-1]) / adim_rot_rate
dcml = (cml - Coef.cml[-1]) / adim_rot_rate
dcmd = (cmd - Coef.cmd[-1]) / adim_rot_rate
dcms = (cms - Coef.cms[-1]) / adim_rot_rate
Coef.damping_derivatives.add_damping_der_coef(
dcl, dcd, dcs, dcml, dcmd, dcms, '_dr')
elif '_TED_' in config_dir:
config_dir_split = config_dir.split('_')
ted_idx = config_dir_split.index('TED')
ted_uid = config_dir_split[ted_idx + 1]
defl_angle = float(config_dir.split('_defl')[1])
try:
print(Coef.IncrMap.dcl)
except AttributeError:
Coef.IncrMap = apmf.IncrementMap(ted_uid)
# TODO: still in development, for now only 1 ted and 1 defl
print(ted_uid, defl_angle)
dcl = (cl - Coef.cl[-1])
dcd = (cd - Coef.cd[-1])
dcs = (cs - Coef.cs[-1])
dcml = (cml - Coef.cml[-1])
dcmd = (cmd - Coef.cmd[-1])
dcms = (cms - Coef.cms[-1])
control_parameter = -1
Coef.IncrMap.add_cs_coef(dcl, dcd, dcs, dcml, dcmd, dcms,
ted_uid, control_parameter)
else: # No damping derivative or control surfaces case
Coef.add_coefficients(cl, cd, cs, cml, cmd, cms)
if check_extract_loads:
results_files_dir = os.path.join(wkdir, config_dir)
extract_loads(results_files_dir)
os.chdir(wkdir)
# Save object Coef in the CPACS file
apmf.save_coefficients(tixi, aeromap_uid, Coef)
cpsf.close_tixi(tixi, cpacs_out_path)