def main():
# Init TiXI
tixi_h = tixiwrapper.Tixi()
tixi_h.open('toolOutput.xml')
# Init TiGL
tigl_h = tiglwrapper.Tigl()
tigl_h.open(tixi_h, 'AircraftModel')
# Extract wing:
mgr = CCPACSConfigurationManager_get_instance()
aircraft_config = mgr.get_configuration(tigl_h._handle.value)
wing = aircraft_config.get_wing("wing")
wing_shape = wing.get_loft().shape()
# Do the slicing:
wing_section = slicing(wing_shape, 0.5)
# Discretize the section:
pnts, face_ids = discretize(wing_section, 1e-5)
# Plot results:
display, start_display, add_menu, add_function_to_menu = init_display()
display.DisplayShape(wing_shape, transparency=0.8, update=True)
display.DisplayShape(wing_section, color='red', update=True)
start_display()
plt.plot(pnts[:, 0], pnts[:, 2], '.')
plt.show()
def initialize(file):
global tixi, tigl
from tixi import tixiwrapper
from tigl import tiglwrapper
tixi = tixiwrapper.Tixi()
tixi.open(file)
tigl = tiglwrapper.Tigl()
tigl.open(tixi, 'AircraftModel')
from . import utils
global_namespace = globals()
for function in __all__:
global_namespace[function] = getattr(utils, function)
return tixi, tigl
def convert_geometry(filename, new_cpacs_file, old_cpacs_file):
"""
Geometric conversion main routine
:return:
"""
tigl2 = tiglwrapper.Tigl()
logging.info("Loading CPACS-2 file '" + filename + "' with TiGL 2")
tigl2.open(old_cpacs_file, "")
logging.info("Loading CPACS-3 file with TiGL 3")
tigl3 = tigl3wrapper.Tigl3()
tigl3.open(new_cpacs_file, "")
convert_guide_curve_points(new_cpacs_file, old_cpacs_file, tigl2, tigl3)
convert_eta_xsi_values(new_cpacs_file, tigl2, tigl3)
# -*- coding: utf-8 -*-
"""
Please read the function`s docstring :)
"""
import math
import bisect
import numpy as np
from tixi import tixiwrapper
from tigl import tiglwrapper
tixi = tixiwrapper.Tixi()
tixi.open('./aircraft.xml')
tigl = tiglwrapper.Tigl()
tigl.open(tixi, 'AircraftModel')
def get_airfoil_points(wing_uid, eta, npoints=25, *, method='geometric',
joint=True, normalize=False):
"""
Extracts an airfoil of the wing section defined by a relative coordinate eta.
Parameters
----------
wing_uid : string
uID of the wing ('wing', 'htp', 'vtp').
eta : float
Relative coordinate in spanwise direction, must be in range of [0, 1].
npoints : integer, optional
Number of points along upper/lower airfoil curve. (Default: 25)
method : string, optional
mirrored_shape = segment.get_mirrored_loft()
if mirrored_shape is not None:
display.DisplayShape(mirrored_shape.shape(), update=True)
for iobj in range(1, config.get_external_object_count() + 1):
obj = config.get_external_object(iobj)
shape = obj.get_loft()
if shape is not None:
display.DisplayShape(shape.shape(), update=True)
mirrored_shape = obj.get_mirrored_loft()
if mirrored_shape is not None:
display.DisplayShape(mirrored_shape.shape(), update=True)
display.FitAll()
start_display()
if __name__ == '__main__':
tixi_h = tixiwrapper.Tixi()
tigl_h = tiglwrapper.Tigl()
dir_path = os.path.dirname(os.path.realpath(__file__))
tixi_h.open(dir_path + "/../../tests/TestData/D150_v201.xml")
tigl_h.open(tixi_h, "")
display_configuration(tigl_h)