pack_coord method in Coordinates

1 files changed, 26 insertions, 13 deletions

diff --git a/creator.py b/creator.py
index 953f088..673cfe9 100644
--- a/creator.py
+++ b/creator.py
@@ -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])