add example

1 files changed, 0 insertions, 121 deletions

diff --git a/main.py b/main.py
deleted file mode 100644
index c0d90ae..0000000
--- a/main.py
+++ /dev/null
@@ -1,121 +0,0 @@
-# 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  # Create geometry
-import evaluator  # Evaluate geometry
-import generator  # Iteratevely evaluate instances of geometry and optimize
-import numpy as np
-
-import time
-start_time = time.time()
-
-# Airfoil dimensions
-NACA_NUM = 2412
-CHORD_LENGTH = 2  # inches
-SEMI_SPAN = 150  # inches
-
-# Thicknesses
-SPAR_THICKNESS = 0.4
-SKIN_THICKNESS = 0.1
-
-# Component masses
-AIRFOIL_MASS = 10  # lbs
-SPAR_MASS = 10  # lbs
-STRINGER_MASS = 5  # lbs
-
-# Area
-SPAR_CAP_AREA = 0.3  # sqin
-STRINGER_AREA = 0.1  # sqin
-
-# Amount of stringers
-TOP_STRINGERS = 6
-BOTTOM_STRINGERS = 4
-NOSE_TOP_STRINGERS = 3
-NOSE_BOTTOM_STRINGERS = 5
-
-# population information & save path
-POP_SIZE = 1
-SAVE_PATH = 'C:/Users/blend/github/UCLA_MAE_154B/save'
-
-
-def main():
-    """
-    Create an airfoil;
-    Evaluate an airfoil;
-    Generate a population of airfoils & optimize.
-    """
-
-    # Interate through all wings in population, creating and evaluating them.
-    for _ in range(1, POP_SIZE + 1):
-
-        # Create airfoil instance
-        af = creator.Airfoil.from_dimensions(CHORD_LENGTH, SEMI_SPAN)
-        # Define NACA airfoil coordinates and mass
-        af.add_naca(NACA_NUM)
-        af.add_mass(AIRFOIL_MASS)
-        # af.info_print(2)
-        af.info_save(SAVE_PATH, _)
-
-        # Create spar instance
-        af.spar = creator.Spar()
-        # Define the spar coordinates and mass, stored in single spar object
-        af.spar.add_coord(af, 0.23)
-        af.spar.add_coord(af, 0.57)
-        # Automatically adds spar caps for each spar defined previously
-        af.spar.add_spar_caps(SPAR_CAP_AREA)
-        af.spar.add_mass(SPAR_MASS)
-        af.spar.add_webs(SPAR_THICKNESS)
-        # af.spar.info_print(2)
-        af.spar.info_save(SAVE_PATH, _)
-
-        # Create stringer instance
-        af.stringer = creator.Stringer()
-        # Compute the stringer coordinates from their quantity in each zone
-        af.stringer.add_coord(af,
-                              NOSE_TOP_STRINGERS,
-                              TOP_STRINGERS,
-                              NOSE_BOTTOM_STRINGERS,
-                              BOTTOM_STRINGERS)
-        af.stringer.add_area(STRINGER_AREA)
-        af.stringer.add_mass(STRINGER_MASS)
-        af.stringer.add_webs(SKIN_THICKNESS)
-        # af.stringer.info_print(2)
-        af.stringer.info_save(SAVE_PATH, _)
-
-        # Plot components with matplotlib
-        # creator.plot_geom(af, True)
-
-        # Evaluator object contains airfoil analysis results.
-        eval = evaluator.Evaluator(af)
-        # The analysis is performed in the evaluator.py module.
-        eval.analysis(1, 1)
-        # eval.info_print(2)
-        eval.info_save(SAVE_PATH, _)
-        # evaluator.plot_geom(eval)
-        # evaluator.plot_lift(eval)
-
-        pop = generator.Population(10)
-
-        # print(help(creator))
-        # print(help(evaluator))
-        # print(help(generator))
-
-    # Print final execution time
-    print("--- %s seconds ---" % (time.time() - start_time))
-
-
-if __name__ == '__main__':
-    main()