diff options
Diffstat (limited to 'creator.py')
| -rw-r--r-- | creator.py | 39 |
1 files changed, 26 insertions, 13 deletions
@@ -59,11 +59,12 @@ class Coordinates: self.x_l = []
self.y_l = []
# Coordinates x_u, y_u, x_l, y_l packed in single list
- self.coordinates = []
+ self.coord = []
+ # The airfoil components know the Coordinates instance's coords
global parent
parent = self
- def print_coord(self, round):
+ def print_component(self, round):
"""
Print all the component's coordinates to the terminal.
@@ -100,6 +101,12 @@ class Coordinates: self.print_coord(4)
return None
+ def pack_coord(self):
+ self.coord.append(self.x_u)
+ self.coord.append(self.y_u)
+ self.coord.append(self.x_l)
+ self.coord.append(self.y_l)
+
class Airfoil(Coordinates):
"""This class enables the creation of a single NACA airfoil."""
@@ -227,11 +234,7 @@ class Airfoil(Coordinates): self.x_l.append(get_lower_coordinates(x)[0])
self.y_l.append(get_lower_coordinates(x)[1])
- self.coordinates.append(self.x_u)
- self.coordinates.append(self.y_u)
- self.coordinates.append(self.x_l)
- self.coordinates.append(self.y_l)
-
+ super().pack_coord()
return None
@@ -271,6 +274,8 @@ class Spar(Coordinates): self.y_u.append(y_u[spar_x_u])
self.x_l.append(x_l[spar_x_l])
self.y_l.append(y_l[spar_x_l])
+
+ super().pack_coord()
return None
@@ -281,17 +286,25 @@ class Stringer(): def __init__(self):
super().__init__(parent.chord, parent.semi_span)
- def add_stringer(self, *density):
+ def add_stringer(self, coordinates, den_u_1, den_u_2, den_l_1, den_l_2):
"""
- Add stringers to the wing from their distribution density between spars.
- First half of density[] concerns stringer distribution on
+ Add stringers to the wing from their density distribution.
Parameters:
- material: stringer material
- *density:
+ den_u_1: upper nose stringer density (until first spar)
+ den_u_2: upper surface stringer density
+ den_l_1: lower nose stringer density (until first spar)
+ den_l_2: lower surface stringer density
+ Returns:
+ None
"""
-
+ # Airfoil surface coordinates
+ # unpacked from 'coordinates' (list of lists in 'Airfoil').
+ x_u = coordinates[0]
+ y_u = coordinates[1]
+ x_l = coordinates[2]
+ y_l = coordinates[3]
# Find interval between leading edge and first upper stringer,
# from density parameter den_u_1.
interval = self.spar_x_u[0] / (den_u_1 * self.spar_x_u[0])
|