ENH: add title to some fins plots

Author: MateusStano

rocketpy/plots/aero_surface_plots.py

@@ -164,7 +164,6 @@ def roll(self):
         None
         """
         print("Roll parameters:")
-        # TODO: lacks a title in the plots
         self.aero_surface.roll_parameters[0]()
         self.aero_surface.roll_parameters[1]()
 
@@ -226,7 +225,6 @@ def roll(self):
         None
         """
         print("Roll parameters:")
-        # TODO: lacks a title in the plots
         self.aero_surface.roll_parameters[0]()
         self.aero_surface.roll_parameters[1]()
 

rocketpy/rocket/aero_surface/fins/_base_fin.py

@@ -128,6 +128,7 @@ def evaluate_single_fin_lift_coefficient(self):
             # for the specific airfoil
             self.airfoil_cl = Function(
                 self.airfoil[0],
+                title="Airfoil lift coefficient",
                 interpolation="linear",
             )
 

rocketpy/rocket/aero_surface/fins/fin.py

@@ -4,9 +4,7 @@
 
 from rocketpy.mathutils.function import Function
 from rocketpy.mathutils.vector_matrix import Matrix, Vector
-from rocketpy.rocket.aero_surface.fins.base_fin import _BaseFin
-
-from ..aero_surface import AeroSurface
+from rocketpy.rocket.aero_surface.fins._base_fin import _BaseFin
 
 
 class Fin(_BaseFin):
@@ -225,7 +223,17 @@ def evaluate_roll_parameters(self):
             roll moment damping coefficient and the cant angle in
             radians
         """
-        clf_delta = 0  # Not used in this class
+        clf_delta = (
+            self.roll_forcing_interference_factor
+            * (self.Yma + self.rocket_radius)
+            * self.clalpha_single_fin
+            / self.reference_length
+        )  # Function of mach number
+        clf_delta.set_inputs("Mach")
+        clf_delta.set_outputs("Roll moment forcing coefficient derivative")
+        clf_delta.set_title(
+            "Roll moment forcing coefficient derivative vs. Mach number"
+        )
         cld_omega = -(
             2
             * self.roll_damping_interference_factor
@@ -236,6 +244,9 @@ def evaluate_roll_parameters(self):
         )  # Function of mach number
         cld_omega.set_inputs("Mach")
         cld_omega.set_outputs("Roll moment damping coefficient derivative")
+        cld_omega.set_title(
+            "Roll moment damping coefficient derivative vs. Mach number"
+        )
         self.roll_parameters = [clf_delta, cld_omega, self.cant_angle_rad]
         return self.roll_parameters
 

rocketpy/rocket/aero_surface/fins/fins.py

@@ -1,7 +1,7 @@
 import numpy as np
 
 from rocketpy.mathutils.function import Function
-from rocketpy.rocket.aero_surface.fins.base_fin import _BaseFin
+from rocketpy.rocket.aero_surface.fins._base_fin import _BaseFin
 
 from ..aero_surface import AeroSurface
 
@@ -209,6 +209,9 @@ def evaluate_roll_parameters(self):
         )  # Function of mach number
         clf_delta.set_inputs("Mach")
         clf_delta.set_outputs("Roll moment forcing coefficient derivative")
+        clf_delta.set_title(
+            "Roll moment forcing coefficient derivative vs. Mach number"
+        )
         cld_omega = -(
             2
             * self.roll_damping_interference_factor
@@ -220,6 +223,9 @@ def evaluate_roll_parameters(self):
         )  # Function of mach number
         cld_omega.set_inputs("Mach")
         cld_omega.set_outputs("Roll moment damping coefficient derivative")
+        cld_omega.set_title(
+            "Roll moment damping coefficient derivative vs. Mach number"
+        )
         self.roll_parameters = [clf_delta, cld_omega, self.cant_angle_rad]
         return self.roll_parameters