ENH: Add tube-fin aerodynamic surface

docs/reference/classes/aero_surfaces/TubeFins.rst

@@ -0,0 +1,5 @@
+TubeFins Class
+==============
+
+.. autoclass:: rocketpy.TubeFins
+   :members:

docs/reference/classes/aero_surfaces/index.rst

@@ -12,11 +12,12 @@ AeroSurface Classes
    TrapezoidalFins
    EllipticalFins
    FreeFormFins
+   TubeFins
    Fin
    TrapezoidalFin
    EllipticalFin
    FreeFormFin
    RailButtons
    AirBrakes
    GenericSurface
-   LinearGenericSurface
+   LinearGenericSurface

docs/technical/aerodynamics/tube_fins.rst

@@ -0,0 +1,87 @@
+Tube Fin Aerodynamics
+=====================
+
+RocketPy models a tube-fin set as a symmetric ring of uncanted ring airfoils.
+The implementation follows the preliminary tube-fin model in OpenRocket's
+`TubeFinSetCalc <https://github.com/openrocket/openrocket/blob/unstable/core/src/main/java/info/openrocket/core/aerodynamics/barrowman/TubeFinSetCalc.java>`_.
+The normal-force derivative is based on Ribner's analysis of a ring airfoil in
+nonaxial flow [1]_.
+
+Geometry
+--------
+
+Let :math:`n` be the number of tubes, :math:`R` the rocket-body radius,
+:math:`r_i` the tube inner radius, :math:`r_o` the tube outer radius, and
+:math:`L` the tube length. The tubes are distributed evenly around the rocket.
+The current implementation requires each tube to touch its two neighbors:
+
+.. math::
+
+   r_o = R \frac{\sin(\pi / n)}{1 - \sin(\pi / n)}.
+
+This constraint also places each tube against the rocket body. Configurations
+with fewer than three tubes, gaps between tubes, or overlapping tubes are
+rejected.
+
+Normal Force
+------------
+
+The ring-airfoil aspect ratio and its modified form are
+
+.. math::
+
+   AR = \frac{2 r_i}{L}, \qquad AR' = \frac{2 AR}{\pi}.
+
+For a rocket reference area :math:`A_{ref} = \pi R^2`, the normal-force
+coefficient derivative of the complete tube set is
+
+.. math::
+
+   C_{N_\alpha} =
+   \frac{n}{A_{ref}}
+   2 \left(\frac{AR'}{1 + AR'}\right) \pi^2 r_i L.
+
+RocketPy applies this derivative symmetrically for positive and negative
+angles of attack and caps the magnitude at 20 degrees:
+
+.. math::
+
+   C_N(\alpha) = C_{N_\alpha}
+   \operatorname{clip}\left(\alpha, -20^\circ, 20^\circ\right).
+
+Center of Pressure
+------------------
+
+For Mach numbers up to 0.5, the center of pressure is placed at the quarter
+chord:
+
+.. math::
+
+   x_{CP} = \frac{L}{4}.
+
+The position is measured from the tube leading edge. OpenRocket moves this
+position with Mach number above Mach 0.5; RocketPy does not yet implement that
+correction. Simulations that exceed Mach 0.5 should use aerodynamic data from a
+higher-fidelity source instead of this fixed-CP model.
+
+Model Limits
+------------
+
+The tube-fin surface contributes normal force and the corresponding pitch and
+yaw moments about its center of pressure. It does not calculate:
+
+- friction or pressure drag from the tubes;
+- roll forcing or damping;
+- side-force or yaw behavior for asymmetric tube layouts;
+- tube cant; or
+- aerodynamic corrections for separated or overlapping tubes.
+
+Represent tube-fin drag in the rocket's power-on and power-off drag curves.
+Use :class:`rocketpy.GenericSurface` when measured, wind-tunnel, or CFD
+coefficients are available outside the limits above.
+
+References
+----------
+
+.. [1] Ribner, H. S. "The Ring Airfoil in Nonaxial Flow." *Journal of the
+   Aeronautical Sciences*, 14(9), 529--530, 1947.

docs/technical/index.rst

@@ -14,9 +14,10 @@ in their code.
    Equations of Motion v1 <equations_of_motion_v1.rst>
    Elliptical Fins <aerodynamics/elliptical_fins.rst>
    Individual Fin <aerodynamics/individual_fins.rst>
+   Tube Fins <aerodynamics/tube_fins.rst>
    Roll Moment <aerodynamics/roll_equations.rst>
    Sensitivity Analysis <sensitivity.rst>
    References <references.rst>
 
 This section is still a work in progress, however, and not everything is documented yet.
-If you have any questions, please contact the maintainers of RocketPy.
+If you have any questions, please contact the maintainers of RocketPy.

docs/user/aerodynamics/surfaces.rst

@@ -7,12 +7,11 @@ Aerodynamic Surfaces
 This page provides an overview of the aerodynamic surfaces available in
 RocketPy and explains how they connect to the rocket's simulation.
 
-RocketPy models the aerodynamic forces and moments generated by three types
-of surfaces: **nose cones**, **fins**, and **tails**. Each surface is
-defined by its geometric parameters and, optionally, by an airfoil profile.
-The aerodynamic coefficients are computed internally using the Barrowman
-method and are used during the flight simulation to evaluate the rocket's
-stability and control.
+RocketPy models the aerodynamic forces and moments generated by **nose
+cones**, **planar fins**, **tube fins**, and **tails**. Each surface is defined
+by its geometric parameters. Planar fins can also use a measured airfoil lift
+curve. The resulting aerodynamic coefficients are used during the flight
+simulation to evaluate the rocket's stability and control.
 
 .. seealso::
 
@@ -112,6 +111,10 @@ RocketPy distinguishes between two levels of fin definition:
   separately. Individual fins are useful for canards, asymmetric
   configurations, or when you need fine-grained control.
 
+- **Tube-fin sets** (:class:`rocketpy.TubeFins`): This class defines a
+  symmetric ring of cylindrical fins. Its normal-force derivative follows
+  Ribner's ring-airfoil model rather than the planar-fin Barrowman equations.
+
 .. seealso::
 
    For the mathematical model of individual fins, including the moment
@@ -178,6 +181,31 @@ Parameters:
 - ``coordinates``: A list of ``(x, y)`` tuples defining the fin shape
   in the fin coordinate frame.
 
+Tube Fins
+~~~~~~~~~
+
+Tube fins are defined by the number and length of the tubes, their inner and
+outer radii, and the rocket-body radius at the mounting position. Add them to a
+rocket with :meth:`rocketpy.Rocket.add_tube_fins` or create a
+:class:`rocketpy.TubeFins` object and pass it to
+:meth:`rocketpy.Rocket.add_surfaces`.
+
+The current implementation is a subsonic normal-force model with these
+limits:
+
+- The center of pressure is fixed at one quarter of the tube length, measured
+  from the leading edge. Use the model only through Mach 0.5.
+- Lift is capped at an absolute angle of attack of 20 degrees.
+- At least three uncanted tubes must be distributed evenly around the body.
+  Every tube must touch the body and both adjacent tubes. Separated and
+  overlapping tube layouts are rejected.
+- The model does not calculate tube-fin friction drag, pressure drag, roll,
+  side force, or yaw. Include tube-fin drag in the rocket's power-on and
+  power-off drag curves.
+
+For the equations and geometry constraint, see
+:doc:`Tube Fin Aerodynamics </technical/aerodynamics/tube_fins>`.
+
 Common Fin Set Parameters
 -------------------------
 
@@ -260,6 +288,7 @@ Fins can be added to a rocket using the ``Rocket`` class methods:
    - :meth:`rocketpy.Rocket.add_trapezoidal_fins`
    - :meth:`rocketpy.Rocket.add_elliptical_fins`
    - :meth:`rocketpy.Rocket.add_free_form_fins`
+   - :meth:`rocketpy.Rocket.add_tube_fins`
    - :meth:`rocketpy.Rocket.add_surfaces` (for individual fins)
 
 Tail

rocketpy/__init__.py

@@ -52,6 +52,7 @@
     Tail,
     TrapezoidalFin,
     TrapezoidalFins,
+    TubeFins,
 )
 from .sensitivity import SensitivityModel
 from .sensors import Accelerometer, Barometer, GnssReceiver, Gyroscope

rocketpy/plots/aero_surface_plots.py

@@ -842,6 +842,41 @@ def draw(self, *, filename=None):
         show_or_save_plot(filename)
 
 
+class _TubeFinsPlots(_AeroSurfacePlots):
+    """Class that contains all tube-fin plots."""
+
+    def draw(self, *, filename=None):
+        """Draw a side-view envelope of the tube-fin set."""
+        axial, radial = self.aero_surface.shape_vec
+        _, ax = plt.subplots()
+
+        ax.plot(axial, radial, color="#A60628", label="Tube-fin envelope")
+        ax.plot(axial, -radial, color="#A60628")
+        ax.plot(
+            [0, self.aero_surface.length],
+            [0, 0],
+            color="#7A68A6",
+            linestyle="--",
+            label="Rocket centerline",
+        )
+
+        cp_point = (self.aero_surface.cpz, 0)
+        ax.scatter(*cp_point, label="Center of Pressure", color="red", zorder=10)
+        ax.scatter(*cp_point, facecolors="none", edgecolors="red", s=300, zorder=10)
+
+        limit = self.aero_surface.rocket_radius + 2 * self.aero_surface.outer_radius
+        ax.set_xlim(-0.02 * self.aero_surface.length, 1.02 * self.aero_surface.length)
+        ax.set_ylim(-1.05 * limit, 1.05 * limit)
+        ax.set_aspect("equal")
+        ax.set_xlabel("Length (m)")
+        ax.set_ylabel("Radius (m)")
+        ax.set_title("Tube Fin Set Side-View Envelope")
+        ax.grid(True, linestyle="--", linewidth=0.5)
+        ax.legend(bbox_to_anchor=(1.05, 1.0), loc="upper left")
+        plt.tight_layout()
+        show_or_save_plot(filename)
+
+
 class _TailPlots(_AeroSurfacePlots):
     """Class that contains all tail plots."""
 

rocketpy/prints/aero_surface_prints.py

@@ -291,6 +291,21 @@ class _FreeFormFinPrints(_FinPrints):
     """Class that contains all free form fins prints."""
 
 
+class _TubeFinsPrints(_AeroSurfacePrints):
+    """Class that contains all tube-fin prints."""
+
+    def geometry(self):
+        """Print the geometric information of the tube-fin set."""
+        print("Geometric information of the tube-fin set:")
+        print("------------------------------------------")
+        print(f"Number of tubes: {self.aero_surface.n}")
+        print(f"Tube length: {self.aero_surface.length:.3f} m")
+        print(f"Inner tube radius: {self.aero_surface.inner_radius:.3f} m")
+        print(f"Outer tube radius: {self.aero_surface.outer_radius:.3f} m")
+        print(f"Reference rocket radius: {self.aero_surface.rocket_radius:.3f} m")
+        print(f"Ring-airfoil aspect ratio: {self.aero_surface.aspect_ratio:.3f}\n")
+
+
 class _TailPrints(_AeroSurfacePrints):
     """Class that contains all tail prints."""
 

rocketpy/rocket/__init__.py

@@ -15,6 +15,7 @@
     Tail,
     TrapezoidalFin,
     TrapezoidalFins,
+    TubeFins,
 )
 from rocketpy.rocket.components import Components
 from rocketpy.rocket.parachute import Parachute

rocketpy/rocket/aero_surface/__init__.py

@@ -15,3 +15,4 @@
 from rocketpy.rocket.aero_surface.nose_cone import NoseCone
 from rocketpy.rocket.aero_surface.rail_buttons import RailButtons
 from rocketpy.rocket.aero_surface.tail import Tail
+from rocketpy.rocket.aero_surface.tube_fins import TubeFins