MNT: small doc changes

rocketpy/rocket/aero_surface/fins/elliptical_fins.py

@@ -106,7 +106,7 @@ def __init__(
         Parameters
         ----------
         n : int
-            Number of fins, from 2 to infinity.
+            Number of fins, must be larger than 2.
         root_chord : int, float
             Fin root chord in meters.
         span : int, float

rocketpy/rocket/aero_surface/fins/fins.py

@@ -106,7 +106,7 @@ def __init__(
         Parameters
         ----------
         n : int
-            Number of fins, from 2 to infinity.
+            Number of fins, must be larger than 2.
         root_chord : int, float
             Fin root chord in meters.
         span : int, float

rocketpy/rocket/aero_surface/fins/free_form_fins.py

@@ -101,7 +101,7 @@ def __init__(
         Parameters
         ----------
         n : int
-            Number of fins, from 2 to infinity.
+            Number of fins, must be larger than 2.
         shape_points : list
             List of tuples (x, y) containing the coordinates of the fin's
             geometry defining points. The point (0, 0) is the root leading edge.

rocketpy/rocket/aero_surface/fins/trapezoidal_fins.py

@@ -111,7 +111,7 @@ def __init__(
         Parameters
         ----------
         n : int
-            Number of fins, from 2 to infinity.
+            Number of fins, must be larger than 2.
         root_chord : int, float
             Fin root chord in meters.
         tip_chord : int, float

rocketpy/rocket/rocket.py

@@ -563,10 +563,10 @@ def evaluate_surfaces_cp_to_cdm(self):
             surface center of pressure to the rocket's center of mass.
         """
         for surface, position in self.aerodynamic_surfaces:
-            self.evaluate_single_surface_cp_to_cdm(surface, position)
+            self.__evaluate_single_surface_cp_to_cdm(surface, position)
         return self.surfaces_cp_to_cdm
 
-    def evaluate_single_surface_cp_to_cdm(self, surface, position):
+    def __evaluate_single_surface_cp_to_cdm(self, surface, position):
         """Calculates the relative position of each aerodynamic surface
         center of pressure to the rocket's center of dry mass in Body Axes
         Coordinate System."""
@@ -996,21 +996,22 @@ def add_surfaces(self, surfaces, positions):
         -------
         None
         """
+        # TODO: separate this method into smaller methods: https://github.com/RocketPy-Team/RocketPy/pull/696#discussion_r1771978422
         try:
             for surface, position in zip(surfaces, positions):
                 if not isinstance(position, (Vector, tuple, list)):
                     position = Vector([0, 0, position])
                 else:
                     position = Vector(position)
                 self.aerodynamic_surfaces.add(surface, position)
-                self.evaluate_single_surface_cp_to_cdm(surface, position)
+                self.__evaluate_single_surface_cp_to_cdm(surface, position)
         except TypeError:
             if not isinstance(positions, (Vector, tuple, list)):
                 positions = Vector([0, 0, positions])
             else:
                 positions = Vector(positions)
             self.aerodynamic_surfaces.add(surfaces, positions)
-            self.evaluate_single_surface_cp_to_cdm(surfaces, positions)
+            self.__evaluate_single_surface_cp_to_cdm(surfaces, positions)
 
         self.evaluate_center_of_pressure()
         self.evaluate_stability_margin()
@@ -1175,7 +1176,7 @@ def add_trapezoidal_fins(
         Parameters
         ----------
         n : int
-            Number of fins, from 2 to infinity.
+            Number of fins, must be greater than 2.
         span : int, float
             Fin span in meters.
         root_chord : int, float
@@ -1273,7 +1274,7 @@ def add_elliptical_fins(
         Parameters
         ----------
         n : int
-            Number of fins, from 2 to infinity.
+            Number of fins, must be greater than 2.
         root_chord : int, float
             Fin root chord in meters.
         span : int, float
@@ -1341,8 +1342,8 @@ def add_free_form_fins(
         Parameters
         ----------
         n : int
-            Number of fins, from 2 to infinity.
-        shape_points : list[tuple[float, float]]
+            Number of fins, must be greater than 2.
+        shape_points : list
             List of tuples (x, y) containing the coordinates of the fin's
             geometry defining points. The point (0, 0) is the root leading edge.
             Positive x is rearwards, positive y is upwards (span direction).

rocketpy/simulation/flight.py

@@ -2704,16 +2704,6 @@ def angle_of_sideslip(self):
         )  # x-z plane
         return np.column_stack([self.time, np.rad2deg(beta)])
 
-    @funcify_method("Time (s)", "Angle of Attack (°)", "spline", "constant")
-    def angle_of_attack2(self):
-        alpha = np.arctan(
-            np.sqrt(
-                np.tan(np.deg2rad(self.partial_angle_of_attack.y_array)) ** 2
-                + np.tan(np.deg2rad(self.angle_of_sideslip.y_array)) ** 2
-            )
-        )
-        return np.column_stack([self.time, np.rad2deg(alpha)])
-
     # Frequency response and stability variables
     @funcify_method("Frequency (Hz)", "ω1 Fourier Amplitude", "spline", "zero")
     def omega1_frequency_response(self):