diff options
| -rw-r--r-- | creator.py | 4 | ||||
| -rw-r--r-- | evaluator.py | 72 | ||||
| -rw-r--r-- | main.py | 20 |
3 files changed, 62 insertions, 34 deletions
@@ -254,6 +254,10 @@ class Spar(Coordinates): self.z_l.append(z_l[spar_x_l]) return None + def add_spar_caps(self, spar_cap_area): + self.cap_area = spar_cap_area + return None + def add_mass(self, mass): self.mass = len(self.x_u) * mass return None diff --git a/evaluator.py b/evaluator.py index 4ab9477..5710522 100644 --- a/evaluator.py +++ b/evaluator.py @@ -27,9 +27,12 @@ class Evaluator: def __init__(self, airfoil): # Evaluator knows all geometrical info from evaluated airfoil self.airfoil = airfoil + self.spar = airfoil.spar + self.stringer = airfoil.stringer # Global dimensions self.chord = airfoil.chord self.semi_span = airfoil.semi_span + # mass and area self.mass_total = float(airfoil.mass + airfoil.spar.mass @@ -41,11 +44,6 @@ class Evaluator: # Lower coordinates self.x_l = airfoil.x_l self.z_l = airfoil.z_l - # Spars - self.spar = airfoil.spar - # Stringers - self.stringer = airfoil.stringer - # Lifts self.lift_rectangular = [] self.lift_elliptical = [] self.lift_total = [] @@ -139,36 +137,52 @@ class Evaluator: def get_centroid(self): '''Return the coordinates of the centroid.''' - area = self.airfoil.stringer.area + stringer_area = self.stringer.area + caps_area = self.spar.cap_area - x_stringers = self.airfoil.stringer.x_u + self.airfoil.stringer.x_l - x_centroid = sum([x * area for x in x_stringers]) / \ - (len(x_stringers) * area) + x_spars = self.spar.x_u + self.spar.x_l + x_stringers = self.stringer.x_u + self.stringer.x_l + z_stringers = self.stringer.z_u + self.stringer.z_l + denom = float(len(x_spars) * caps_area + + len(x_stringers) * stringer_area) - z_stringers = self.airfoil.stringer.z_u + self.airfoil.stringer.z_l - z_centroid = sum([x * area for x in z_stringers]) / \ - (len(x_stringers) * area) - return(x_centroid, z_centroid) + x_ctr = (sum([i * caps_area for i in self.spar.x_u]) + + sum([i * stringer_area for i in x_stringers])) / denom + z_ctr = (sum([i * caps_area for i in self.spar.z_u]) + + sum([i * stringer_area for i in z_stringers])) / denom + return(x_ctr, z_ctr) def get_inertia_terms(self): '''Obtain all inertia terms.''' - area = self.stringer.area + stringer_area = self.stringer.area + caps_area = self.spar.cap_area + + # Adds upper and lower components' coordinates to list x_stringers = self.stringer.x_u + self.stringer.x_l z_stringers = self.stringer.z_u + self.stringer.z_l + x_spars = self.spar.x_u + self.spar.x_l + z_spars = self.spar.z_u + self.spar.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]) - - I_z = sum([area * (x_stringers[_] - self.centroid[0]) ** 2 - for _ in stringer_count]) - - I_xz = sum([area * (z_stringers[_] - self.centroid[1]) - * (x_stringers[_] - self.centroid[0]) - for _ in stringer_count]) + spar_count = range(len(self.spar.x_u)) + + # I_x is the sum of the contributions of the spar caps and stringers + I_x = (sum([caps_area * (z_spars[i] - self.centroid[1]) ** 2 + for i in spar_count]) + + sum([stringer_area * (z_stringers[i] - self.centroid[1]) ** 2 + for i in stringer_count])) + + I_z = (sum([caps_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([caps_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])) return(I_x, I_z, I_xz) @@ -245,8 +259,10 @@ 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 @@ -27,18 +27,24 @@ NACA_NUM = 2412 CHORD_LENGTH = 40 SEMI_SPAN = 50 +# Airfoil thickness +T_UPPER = 0.1 +T_LOWER = 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 = 8 +TOP_STRINGERS = 7 BOTTOM_STRINGERS = 6 NOSE_TOP_STRINGERS = 4 -NOSE_BOTTOM_STRINGERS = 7 +NOSE_BOTTOM_STRINGERS = 5 # population information & save path POP_SIZE = 1 @@ -65,16 +71,18 @@ def main(): af.add_naca(NACA_NUM) af.add_mass(AIRFOIL_MASS) # af.info_print(2) - af.info_save(SAVE_PATH, _) + # 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, 0.15) af.spar.add_coord(af, 0.55) + # Automatically adds spar caps for all spars previously defined + af.spar.add_spar_caps(SPAR_CAP_AREA) af.spar.add_mass(SPAR_MASS) # af.spar.info_print(2) - af.spar.info_save(SAVE_PATH, _) + # af.spar.info_save(SAVE_PATH, _) # Create stringer instance af.stringer = creator.Stringer() @@ -87,7 +95,7 @@ def main(): af.stringer.add_area(STRINGER_AREA) af.stringer.add_mass(STRINGER_MASS) # af.stringer.info_print(2) - af.stringer.info_save(SAVE_PATH, _) + # af.stringer.info_save(SAVE_PATH, _) # Plot components with matplotlib # creator.plot_geom(af) @@ -98,7 +106,7 @@ def main(): eval.analysis() # eval.info_print(2) eval.info_save(SAVE_PATH, _) - # evaluator.plot_geom(eval) + evaluator.plot_geom(eval) # evaluator.plot_lift(eval) # Print final execution time |