diff options
Diffstat (limited to 'evaluator.py')
| -rw-r--r-- | evaluator.py | 142 |
1 files changed, 70 insertions, 72 deletions
diff --git a/evaluator.py b/evaluator.py index 05900e9..44ed434 100644 --- a/evaluator.py +++ b/evaluator.py @@ -12,7 +12,12 @@ # # You should have received a copy of the GNU General Public License # along with this program. If not, see <https://www.gnu.org/licenses/>. - +""" +The 'evaluator' module contains a single Evaluator class, +which knows all the attributes of a specified Airfoil instance, +and contains functions to analyse the airfoil's geometrical +& structural properties. +""" import sys import os.path @@ -22,7 +27,7 @@ import matplotlib.pyplot as plt class Evaluator: - '''Performs structural evaluations for the airfoil passed as argument.''' + """Performs structural evaluations for the airfoil passed as argument.""" def __init__(self, airfoil): # Evaluator knows all geometrical info from evaluated airfoil @@ -32,8 +37,7 @@ class Evaluator: # Global dimensions self.chord = airfoil.chord self.semi_span = airfoil.semi_span - - # mass and area + # Mass & spanwise distribution self.mass_total = float(airfoil.mass + airfoil.spar.mass + airfoil.stringer.mass) @@ -50,18 +54,14 @@ class Evaluator: # centroid self.centroid = [] # Inertia terms: - # I_x = self.I_[0] - # I_z = self.I_[1] - # I_xz = self.I_[2] - self.I_ = [] + self.I_ = {'x': 0, 'z': 0, 'xz': 0} def info_print(self, round): - ''' + """ Print all the component's evaluated data to the terminal. This function's output is piped to the 'save_data' function below. - ''' - + """ name = ' EVALUATOR DATA ' num_of_dashes = len(name) @@ -73,9 +73,9 @@ class Evaluator: print('Total airfoil mass:', self.mass_total) 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('I_x:\n', np.around(self.I_['x'], 3)) + print('I_z:\n', np.around(self.I_['z'], 3)) + print('I_xz:\n', np.around(self.I_['xz'], 3)) print('Spar dP_x:\n', self.spar.dP_x) print('Spar dP_z:\n', self.spar.dP_z) print(num_of_dashes * '-') @@ -91,8 +91,7 @@ class Evaluator: return None def info_save(self, save_path, number): - '''Save all the object's coordinates (must be full path).''' - + """Save all the object's coordinates (must be full path).""" file_name = 'airfoil_{}_eval.txt'.format(number) full_path = os.path.join(save_path, file_name) try: @@ -102,22 +101,22 @@ class Evaluator: sys.stdout = sys.__stdout__ print('Successfully wrote to file {}'.format(full_path)) except IOError: - print('Unable to write {} to specified directory.\n' - .format(file_name), - 'Was the full path passed to the function?') + print( + 'Unable to write {} to specified directory.\n'.format( + file_name), 'Was the full path passed to the function?') return None # All these functions take integer arguments and return lists. def get_lift_rectangular(self, lift): - L_prime = [lift / (self.semi_span * 2) - for x in range(self.semi_span)] + L_prime = [lift / (self.semi_span * 2) for x in range(self.semi_span)] return L_prime def get_lift_elliptical(self, L_0): - L_prime = [L_0 / (self.semi_span * 2) - * sqrt(1 - (y / self.semi_span) ** 2) - for y in range(self.semi_span)] + L_prime = [ + L_0 / (self.semi_span * 2) * sqrt(1 - (y / self.semi_span)**2) + for y in range(self.semi_span) + ] return L_prime def get_lift_total(self): @@ -126,8 +125,7 @@ class Evaluator: return F_z def get_mass_distribution(self, total_mass): - F_z = [total_mass / self.semi_span - for x in range(0, self.semi_span)] + F_z = [total_mass / self.semi_span for x in range(0, self.semi_span)] return F_z def get_drag(self, drag): @@ -143,8 +141,7 @@ class Evaluator: return F_x def get_centroid(self): - '''Return the coordinates of the centroid.''' - + """Return the coordinates of the centroid.""" stringer_area = self.stringer.area cap_area = self.spar.cap_area @@ -163,11 +160,11 @@ class Evaluator: centroid_z = float(sum([z * cap_area for z in caps_z]) + sum([z * stringer_area for z in stringers_z])) centroid_z = centroid_z / denominator - return(centroid_x, centroid_z) - def get_inertia_terms(self): - '''Obtain all inertia terms.''' + return (centroid_x, centroid_z) + def get_inertia_terms(self): + """Obtain all inertia terms.""" stringer_area = self.stringer.area cap_area = self.spar.cap_area @@ -180,72 +177,75 @@ class Evaluator: spar_count = range(len(self.spar.x)) # I_x is the sum of the contributions of the spar caps and stringers - I_x = (sum([cap_area * (z_spars[i] - self.centroid[1]) ** 2 + # TODO: replace list indices with dictionary value + I_x = sum([cap_area * (z_spars[i] - self.centroid[1])**2 + for i in spar_count]) + I_x += sum([stringer_area * (z_stringers[i] - self.centroid[1])**2 + for i in stringer_count]) + + I_z = sum([cap_area * (x_spars[i] - self.centroid[0])**2 + for i in spar_count]) + I_z += sum([stringer_area * (x_stringers[i] - self.centroid[0])**2 + for i in stringer_count]) + + I_xz = sum([cap_area * (x_spars[i] - self.centroid[0]) + * (z_spars[i] - self.centroid[1]) for i in spar_count]) - + sum([stringer_area * (z_stringers[i] - self.centroid[1]) ** 2 - for i in stringer_count])) + I_xz += sum([stringer_area * (x_stringers[i] - self.centroid[0]) + * (z_stringers[i] - self.centroid[1]) + for i in stringer_count]) + return (I_x, I_z, I_xz) - I_z = (sum([cap_area * (x_spars[i] - self.centroid[0]) ** 2 - for i in spar_count]) - + sum([stringer_area * (x_stringers[i] - self.centroid[0]) ** 2 - for i in stringer_count])) - - I_xz = (sum([cap_area * (x_spars[i] - self.centroid[0]) - * (z_spars[i] - self.centroid[1]) - for i in spar_count]) - + sum([stringer_area * (x_stringers[i] - self.centroid[0]) - * (z_stringers[i] - self.centroid[1]) - for i in stringer_count])) + def get_dx(self, component): + return [x - self.centroid[0] for x in component.x_start] - return(I_x, I_z, I_xz) + def get_dz(self, component): + return [x - self.centroid[1] for x in component.x_start] def analysis(self, V_x, V_z): - '''Perform all analysis calculations and store in class instance.''' + """Perform all analysis calculations and store in class instance.""" - def get_dp(xDist, zDist, V_x, V_z, I_x, I_z, I_xz, area): + def get_dP(xDist, zDist, V_x, V_z, I_x, I_z, I_xz, area): denom = float(I_x * I_z - I_xz ** 2) z = float() for _ in range(len(xDist)): - z += float(- area * xDist[_] * (I_x * V_x - I_xz * V_z) + z += float(-area * xDist[_] * (I_x * V_x - I_xz * V_z) / denom - area * zDist[_] * (I_z * V_z - I_xz * V_x) / denom) return z - def get_dx(component): - return [x - self.centroid[0] for x in component.x_start] - - def get_dz(component): - return [x - self.centroid[1] for x in component.x_start] - self.drag = self.get_drag(10) - self.lift_rectangular = self.get_lift_rectangular(13.7) self.lift_elliptical = self.get_lift_elliptical(15) self.lift_total = self.get_lift_total() - self.mass_dist = self.get_mass_distribution(self.mass_total) self.centroid = self.get_centroid() - self.I_ = self.get_inertia_terms() - self.spar.dP_x = get_dp(get_dx(self.spar), get_dz(self.spar), V_x, 0, - self.I_[0], self.I_[1], self.I_[2], + self.I_['x'] = self.get_inertia_terms()[0] + self.I_['z'] = self.get_inertia_terms()[1] + self.I_['xz'] = self.get_inertia_terms()[2] + spar_dx = self.get_dx(self.spar) + spar_dz = self.get_dz(self.spar) + self.spar.dP_x = get_dP(spar_dx, spar_dz, + V_x, 0, + self.I_['x'], self.I_['z'], self.I_['xz'], self.spar.cap_area) - self.spar.dP_z = get_dp(get_dx(self.spar), get_dz(self.spar), 0, V_z, - self.I_[0], self.I_[1], self.I_[2], + self.spar.dP_z = get_dP(spar_dx, spar_dz, + 0, V_z, + self.I_['x'], self.I_['z'], self.I_['xz'], self.spar.cap_area) return None def plot_geom(evaluator): - '''This function plots analysis results over the airfoil's geometry.''' - + """This function plots analysis results over the airfoil's geometry.""" # Plot chord x_chord = [0, evaluator.chord] y_chord = [0, 0] plt.plot(x_chord, y_chord, linewidth='1') # Plot quarter chord - plt.plot(evaluator.chord / 4, 0, '.', color='g', - markersize=24, label='Quarter-chord') + plt.plot(evaluator.chord / 4, 0, + '.', color='g', markersize=24, label='Quarter-chord') # Plot airfoil surfaces x = [0.98 * x for x in evaluator.x] y = [0.98 * z for z in evaluator.z] @@ -281,8 +281,8 @@ def plot_geom(evaluator): plt.ylabel('Z axis') plot_bound = max(evaluator.x) - plt.xlim(- 0.10 * plot_bound, 1.10 * plot_bound) - plt.ylim(- (1.10 * plot_bound / 2), (1.10 * plot_bound / 2)) + 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) @@ -295,10 +295,8 @@ def plot_lift(evaluator): 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_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 |