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# This file is part of Marius Peter's airfoil analysis package (this program).
#
# This program is free software: you can redistribute it and/or modify
# it under the terms of the GNU General Public License as published by
# the Free Software Foundation, either version 3 of the License, or
# (at your option) any later version.
#
# This program is distributed in the hope that it will be useful,
# but WITHOUT ANY WARRANTY; without even the implied warranty of
# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
# GNU General Public License for more details.
#
# You should have received a copy of the GNU General Public License
# along with this program. If not, see <https://www.gnu.org/licenses/>.
import creator
import random
import time
start_time = time.time()
CHORD_LENGTH = 40
SEMI_SPAN = 200
POP_SIZE = 1
SAVE_PATH = 'C:/Users/blend/github/UCLA_MAE_154B/save'
def main():
# Create coordinate system specific to airfoil dimensions.
creator.Coordinates(CHORD_LENGTH, SEMI_SPAN)
# Interate through all wings in population.
for _ in range(1, POP_SIZE + 1):
# Create airfoil instance
af = creator.Airfoil()
# Define NACA airfoil coordinates
af.naca(2412)
# Print coordinates of af to terminal
af.print_coord(4)
# Create spar instance
af.spar = creator.Spar()
# Define the spar coordinates
af.spar.add_spar(af.coordinates, 'aluminium', 0.15)
# Print coordinates of af.spar to terminal
af.spar.print_coord(4)
# Plot components with matplotlib
creator.plot(af, af.spar)
# Save component coordinates
af.save_coord(SAVE_PATH)
af.spar.save_coord(SAVE_PATH)
# Print final execution time
print("--- %s seconds ---" % (time.time() - start_time))
if __name__ == '__main__':
main()
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