Tail Class#

class rocketpy.Tail[source]#

Class that defines a tail. Currently only accepts conical tails.

Note

Local coordinate system: Z axis along the longitudinal axis of symmetry, positive downwards (top -> bottom). Origin located at top of the tail (generally the portion closest to the rocket’s nose).

Variables:

  • Tail.top_radius (int, float) – Radius of the top of the tail. The top radius is defined as the radius of the transversal section that is closest to the rocket’s nose.

  • Tail.bottom_radius (int, float) – Radius of the bottom of the tail.

  • Tail.length (int, float) – Length of the tail. The length is defined as the distance between the top and bottom of the tail. The length is measured along the rocket’s longitudinal axis. Has the unit of meters.

  • Tail.rocket_radius (int, float) – The reference rocket radius used for lift coefficient normalization in meters.

  • Tail.name (str) – Name of the tail. Default is ‘Tail’.

  • Tail.cpx (int, float) – x local coordinate of the center of pressure of the tail.

  • Tail.cpy (int, float) – y local coordinate of the center of pressure of the tail.

  • Tail.cpz (int, float) – z local coordinate of the center of pressure of the tail.

  • Tail.cp (tuple) – Tuple containing the coordinates of the center of pressure of the tail.

  • Tail.cl (Function) – Function that returns the lift coefficient of the tail. The function is defined as a function of the angle of attack and the mach number.

  • Tail.clalpha (float) – Lift coefficient slope. Has the unit of 1/rad.

  • Tail.slant_length (float) – Slant length of the tail. The slant length is defined as the distance between the top and bottom of the tail. The slant length is measured along the tail’s slant axis. Has the unit of meters.

  • Tail.surface_area (float) – Surface area of the tail. Has the unit of meters squared.

__init__(top_radius, bottom_radius, length, rocket_radius, name='Tail')[source]#

Initializes the tail object by computing and storing the most important values.

Parameters:

  • top_radius (int, float) – Radius of the top of the tail. The top radius is defined as the radius of the transversal section that is closest to the rocket’s nose.

  • bottom_radius (int, float) – Radius of the bottom of the tail.

  • length (int, float) – Length of the tail.

  • rocket_radius (int, float) – The reference rocket radius used for lift coefficient normalization.

  • name (str) – Name of the tail. Default is ‘Tail’.

Return type:

None

evaluate_geometrical_parameters()[source]#

Calculates and saves tail’s slant length and surface area.

Return type:

None

evaluate_lift_coefficient()[source]#

Calculates and returns tail’s lift coefficient. The lift coefficient is saved and returned. This function also calculates and saves its lift coefficient derivative.

Return type:

None

evaluate_center_of_pressure()[source]#

Calculates and returns the center of pressure of the tail in local coordinates. The center of pressure position is saved and stored as a tuple.

Return type:

None

info()[source]#

Prints and plots summarized information of the aerodynamic surface.

Return type:

None

all_info()[source]#

Prints and plots all the available information of the aero surface.

Return type:

None