Merge branch 'master' into develop

Author: phmbressan

CHANGELOG.md

@@ -52,6 +52,18 @@ Attention: The newest changes should be on top -->
 - BUG: Pressure ISA Extrapolation as "linear" [#675](https://github.com/RocketPy-Team/RocketPy/pull/675)
 - BUG: fix the Frequency Response plot of Flight class [#653](https://github.com/RocketPy-Team/RocketPy/pull/653)
 
+## [v1.4.3] - 2024-09-11
+
+You can install this version by running `pip install rocketpy==1.4.3`
+
+### Changed
+
+- REL: Bump versioning to RocketPy v1.4.3 [#687](https://github.com/RocketPy-Team/RocketPy/pull/687)
+
+### Fixed
+
+- BUG: Rollback Prandtl-Glauert corrections for Tail and Nose. [#685](https://github.com/RocketPy-Team/RocketPy/pull/685)
+
 ## [v1.4.2] - 2024-08-03
 
 You can install this version by running `pip install rocketpy==1.4.2`

docs/conf.py

@@ -27,7 +27,7 @@
 author = "RocketPy Team"
 
 # The full version, including alpha/beta/rc tags
-release = "1.4.2"
+release = "1.4.3"
 
 
 # -- General configuration ---------------------------------------------------

docs/user/installation.rst

@@ -19,7 +19,7 @@ If you want to choose a specific version to guarantee compatibility, you may ins
 
 .. code-block:: shell
 
-    pip install rocketpy==1.4.2
+    pip install rocketpy==1.4.3
 
 
 Optional Installation Method: ``conda``

pyproject.toml

@@ -1,6 +1,6 @@
 [project]
 name = "rocketpy"
-version = "1.4.2"
+version = "1.4.3"
 description="Advanced 6-DOF trajectory simulation for High-Power Rocketry."
 dynamic = ["dependencies"]
 readme = "README.md"

rocketpy/rocket/aero_surface/nose_cone.py

@@ -451,7 +451,7 @@ def evaluate_lift_coefficient(self):
         # It must be set as a Function because it will be called and treated
         # as a function of mach in the simulation.
         self.clalpha = Function(
-            lambda mach: 2 / self._beta(mach) * self.radius_ratio**2,
+            lambda mach: 2 * self.radius_ratio**2,
             "Mach",
             f"Lift coefficient derivative for {self.name}",
         )

rocketpy/rocket/aero_surface/tail.py

@@ -169,7 +169,6 @@ def evaluate_lift_coefficient(self):
         # as a function of mach in the simulation.
         self.clalpha = Function(
             lambda mach: 2
-            / self._beta(mach)
             * (
                 (self.bottom_radius / self.rocket_radius) ** 2
                 - (self.top_radius / self.rocket_radius) ** 2

tests/unit/test_flight.py

@@ -167,9 +167,9 @@ def test_out_of_rail_stability_margin(flight_calisto_custom_wind):
 @pytest.mark.parametrize(
     "flight_time, expected_values",
     [
-        ("t_initial", (0.258818, -0.649515, 0)),
-        ("out_of_rail_time", (0.788918, -1.979828, 0)),
-        ("apogee_time", (-0.522394, -0.744154, 0)),
+        ("t_initial", (0.25886, -0.649623, 0)),
+        ("out_of_rail_time", (0.792028, -1.987634, 0)),
+        ("apogee_time", (-0.522875, -0.741825, 0)),
         ("t_final", (0, 0, 0)),
     ],
 )
@@ -206,10 +206,10 @@ def test_aerodynamic_moments(flight_calisto_custom_wind, flight_time, expected_v
 @pytest.mark.parametrize(
     "flight_time, expected_values",
     [
-        ("t_initial", (1.6542528, 0.65918, -0.067107)),
-        ("out_of_rail_time", (5.05334, 2.01364, -1.7541)),
-        ("apogee_time", (2.354663, -1.652953, -0.936126)),
-        ("t_final", (0, 0, 159.2212)),
+        ("t_initial", (1.654150, 0.659142, -0.067103)),
+        ("out_of_rail_time", (5.052628, 2.013361, -1.75370)),
+        ("apogee_time", (2.339424, -1.648934, -0.938867)),
+        ("t_final", (0, 0, 159.2210)),
     ],
 )
 def test_aerodynamic_forces(flight_calisto_custom_wind, flight_time, expected_values):
@@ -246,12 +246,12 @@ def test_aerodynamic_forces(flight_calisto_custom_wind, flight_time, expected_va
     "flight_time, expected_values",
     [
         ("t_initial", (0, 0, 0)),
-        ("out_of_rail_time", (0, 2.248727, 25.703072)),
+        ("out_of_rail_time", (0, 2.248540, 25.700928)),
         (
             "apogee_time",
-            (-14.485655, 15.580647, -0.000240),
+            (-14.488364, 15.638049, -0.000191),
         ),
-        ("t_final", (5, 2, -5.65998)),
+        ("t_final", (5, 2, -5.660155)),
     ],
 )
 def test_velocities(flight_calisto_custom_wind, flight_time, expected_values):
@@ -287,9 +287,9 @@ def test_velocities(flight_calisto_custom_wind, flight_time, expected_values):
     "flight_time, expected_values",
     [
         ("t_initial", (0, 0, 0)),
-        ("out_of_rail_time", (0, 7.8068, 89.2325)),
-        ("apogee_time", (0.07534, -0.058127, -9.614386)),
-        ("t_final", (0, 0, 0.0017346294117130806)),
+        ("out_of_rail_time", (0, 7.8067, 89.2315)),
+        ("apogee_time", (0.07649, -0.053530, -9.620037)),
+        ("t_final", (0, 0, 0.0019548)),
     ],
 )
 def test_accelerations(flight_calisto_custom_wind, flight_time, expected_values):
@@ -337,10 +337,10 @@ def test_rail_buttons_forces(flight_calisto_custom_wind):
     """
     test = flight_calisto_custom_wind
     atol = 5e-3
-    assert pytest.approx(1.825283, abs=atol) == test.max_rail_button1_normal_force
-    assert pytest.approx(0.727335, abs=atol) == test.max_rail_button1_shear_force
-    assert pytest.approx(3.229578, abs=atol) == test.max_rail_button2_normal_force
-    assert pytest.approx(1.286915, abs=atol) == test.max_rail_button2_shear_force
+    assert pytest.approx(1.795539, abs=atol) == test.max_rail_button1_normal_force
+    assert pytest.approx(0.715483, abs=atol) == test.max_rail_button1_shear_force
+    assert pytest.approx(3.257089, abs=atol) == test.max_rail_button2_normal_force
+    assert pytest.approx(1.297878, abs=atol) == test.max_rail_button2_shear_force
 
 
 def test_max_values(flight_calisto_robust):