diff options
| -rw-r--r-- | creator.py | 8 | ||||
| -rw-r--r-- | evaluator.py | 81 | ||||
| -rw-r--r-- | main.py | 15 |
3 files changed, 72 insertions, 32 deletions
@@ -362,7 +362,7 @@ class Stringer(Coordinates): return None -def plot(airfoil): +def plot_geom(airfoil): '''This function plots the airfoil's + sub-components' geometry.''' # Plot chord @@ -370,11 +370,12 @@ def plot(airfoil): y_chord = [0, 0] plt.plot(x_chord, y_chord, linewidth='1') # Plot quarter chord - plt.plot(airfoil.chord / 4, 0, '.', color='g', markersize=24) + plt.plot(airfoil.chord / 4, 0, '.', color='g', + markersize=24, label='Quarter-chord') # Plot mean camber line plt.plot(airfoil.x_c, airfoil.y_c, '-.', color='r', linewidth='2', - label='mean camber line') + label='Mean camber line') # Plot upper surface plt.plot(airfoil.x_u, airfoil.z_u, '', color='b', linewidth='1') @@ -407,6 +408,7 @@ def plot(airfoil): plt.xlim(- 0.10 * plot_bound, 1.10 * plot_bound) plt.ylim(- (1.10 * plot_bound / 2), (1.10 * plot_bound / 2)) plt.gca().set_aspect('equal', adjustable='box') + plt.gca().legend() plt.grid(axis='both', linestyle=':', linewidth=1) plt.show() return None diff --git a/evaluator.py b/evaluator.py index c350974..4ab9477 100644 --- a/evaluator.py +++ b/evaluator.py @@ -25,8 +25,8 @@ class Evaluator: '''Performs structural evaluations for the airfoil passed as argument.''' def __init__(self, airfoil): + # Evaluator knows all geometrical info from evaluated airfoil self.airfoil = airfoil - print(self.airfoil) # Global dimensions self.chord = airfoil.chord self.semi_span = airfoil.semi_span @@ -48,10 +48,14 @@ class Evaluator: # Lifts self.lift_rectangular = [] self.lift_elliptical = [] - self.lift = [] - + self.lift_total = [] # Drag self.drag = [] + # Inertia terms: + # I_x = self.I_[0] + # I_z = self.I_[1] + # I_xz = self.I_[2] + self.I_ = [] def info_print(self, round): ''' @@ -69,20 +73,24 @@ class Evaluator: print('Chord length:', self.chord) print('Semi-span:', self.semi_span) print('Total airfoil mass:', self.mass_total) - print('Centroid location:', np.around(self.centroid, round + 1)) + print('Centroid location:\n', np.around(self.centroid, 3)) + print('Inertia terms:') + print('I_x:\n', np.around(self.I_[0], 3)) + print('I_z:\n', np.around(self.I_[1], 3)) + print('I_xz:\n', np.around(self.I_[2], 3)) print(num_of_dashes * '-') print('Rectangular lift:\n', np.around(self.lift_rectangular, round)) print('Elliptical lift:\n', np.around(self.lift_elliptical, round)) - print('Combined lift:\n', np.around(self.lift, round)) + print('Combined lift:\n', np.around(self.lift_total, round)) print('Distribution of mass:\n', np.around(self.mass_dist, round)) print('Drag:\n', np.around(self.drag, round)) return None - def info_save(self, save_dir_path, number): + def info_save(self, save_path, number): '''Save all the object's coordinates (must be full path).''' file_name = 'airfoil_{}_eval.txt'.format(number) - full_path = os.path.join(save_dir_path, file_name) + full_path = os.path.join(save_path, file_name) try: with open(full_path, 'w') as sys.stdout: self.info_print(6) @@ -142,35 +150,44 @@ class Evaluator: (len(x_stringers) * area) return(x_centroid, z_centroid) - def get_I_x(self): - I_x = float() - i_x = int() - print(I_x) + def get_inertia_terms(self): + '''Obtain all inertia terms.''' + + area = self.stringer.area + x_stringers = self.stringer.x_u + self.stringer.x_l + z_stringers = self.stringer.z_u + self.stringer.z_l + stringer_count = range(len(x_stringers)) + + # I_x is the sum of (stringer area * z-distance to the centroid) ** 2, + # for all stringers. + I_x = sum([area * (z_stringers[_] - self.centroid[1]) ** 2 + for _ in stringer_count]) - def get_I_z(self): - pass + I_z = sum([area * (x_stringers[_] - self.centroid[0]) ** 2 + for _ in stringer_count]) - def get_I_xz(self): - pass + I_xz = sum([area * (z_stringers[_] - self.centroid[1]) + * (x_stringers[_] - self.centroid[0]) + for _ in stringer_count]) + + return(I_x, I_z, I_xz) def analysis(self): '''Perform all analysis calculations and store in class instance.''' self.drag = self.get_drag(10) - self.lift_rectangular = self.get_lift_rectangular(10) + self.lift_rectangular = self.get_lift_rectangular(1000) self.lift_elliptical = self.get_lift_elliptical(15) - self.lift = self.get_lift_total() + self.lift_total = self.get_lift_total() self.mass_dist = self.get_mass_distribution(self.mass_total) self.centroid = self.get_centroid() - self.I_x = self.get_I_x() - self.I_z = self.get_I_z() - self.I_xz = self.get_I_xz() + self.I_ = self.get_inertia_terms() return None -def plot(evaluator): +def plot_geom(evaluator): '''This function plots analysis results over the airfoil's geometry.''' # Plot chord @@ -179,7 +196,7 @@ def plot(evaluator): plt.plot(x_chord, y_chord, linewidth='1') # Plot quarter chord q = evaluator.chord / 4 - plt.plot(q, 0, '.', color='g', markersize=24, label='quarter-chord') + plt.plot(q, 0, '.', color='g', markersize=24, label='Quarter-chord') # Plot upper surface plt.plot(evaluator.x_u, evaluator.z_u, '', color='b', linewidth='1') @@ -217,6 +234,26 @@ def plot(evaluator): plt.xlim(- 0.10 * plot_bound, 1.10 * plot_bound) plt.ylim(- (1.10 * plot_bound / 2), (1.10 * plot_bound / 2)) plt.gca().set_aspect('equal', adjustable='box') + plt.gca().legend() + plt.grid(axis='both', linestyle=':', linewidth=1) + plt.show() + return None + + +def plot_lift(evaluator): + x = range(evaluator.semi_span) + y_1 = evaluator.lift_rectangular + y_2 = evaluator.lift_elliptical + y_3 = evaluator.lift_total + plt.plot(x, y_1, '.', color='b', markersize=4, label='Rectangular lift') + plt.plot(x, y_2, '.', color='g', markersize=4, label='Elliptical lift') + plt.plot(x, y_3, '.', color='r', markersize=4, label='Total lift') + + # Graph formatting + plt.xlabel('Semi-span location') + plt.ylabel('Lift') + + plt.gca().legend() plt.grid(axis='both', linestyle=':', linewidth=1) plt.show() return None @@ -63,7 +63,7 @@ def main(): # Define NACA airfoil coordinates and mass af.add_naca(NACA_NUM) af.add_mass(AIRFOIL_MASS) - af.info_print(2) + # af.info_print(2) af.info_save(SAVE_PATH, _) # Create spar instance @@ -72,7 +72,7 @@ def main(): af.spar.add_coord(af.coord, 0.15) af.spar.add_coord(af.coord, 0.55) af.spar.add_mass(SPAR_MASS) - af.spar.info_print(2) + # af.spar.info_print(2) af.spar.info_save(SAVE_PATH, _) # Create stringer instance @@ -85,19 +85,20 @@ def main(): BOTTOM_STRINGERS) af.stringer.add_area(STRINGER_AREA) af.stringer.add_mass(STRINGER_MASS) - af.stringer.info_print(2) + # af.stringer.info_print(2) af.stringer.info_save(SAVE_PATH, _) # Plot components with matplotlib - creator.plot(af) + # creator.plot_geom(af) - # evaluator.Evaluator instance contains airfoil analysis results. + # Evaluator object contains airfoil analysis results. eval = evaluator.Evaluator(af) # The analysis is performed in the evaluator.py module. eval.analysis() - eval.info_print(2) + # eval.info_print(2) eval.info_save(SAVE_PATH, _) - evaluator.plot(eval) + # evaluator.plot_geom(eval) + # evaluator.plot_lift(eval) # Print final execution time print("--- %s seconds ---" % (time.time() - start_time)) |