flight_mech.aerodynamics module#
Module to define functions to compute aerodynamic effects.
- flight_mech.aerodynamics.check_turbulent_transition(x: float | ndarray, velocity: float | ndarray, nu: float)[source]#
Check if a velocity distribution along a plate has a turbulent transition.
- Parameters:
x (float | np.ndarray) – Array of coordinates along the plate.
velocity (float | np.ndarray) – Array of velocity values.
nu (float) – Kinematic viscosity.
- Raises:
ValueError – Raise error if turbulent transition.
- flight_mech.aerodynamics.compute_blasius_linear_drag(x_array: ndarray, velocity_array: ndarray, rho: float, nu: float, return_array: bool = False)[source]#
Compute the linear drag under the flat rectangle, uniform velocity hypothesis with Blasius’ equation.
- Parameters:
x_array (np.ndarray) – Array of x coordinates along the airfoil.
velocity_array (np.ndarray) – Array of external velocity along the airfoil.
rho (float) – Density of the fluid.
nu (float) – Kinematic viscosity of the fluid.
- Returns:
Linear drag.
- Return type:
float
- flight_mech.aerodynamics.compute_blasius_rectangle_drag(width: float, length: float, velocity: float, rho: float, nu: float)[source]#
Compute drag produced by the upper face of a rectangle with no incidence at the given velocity.
- Parameters:
width (float) – Width of the rectangle.
length (float) – Length of the rectangle.
velocity (float) – Velocity of the rectangle.
rho (float) – Density of the fluid.
nu (float) – Kinematic viscosity of the fluid.
- Returns:
Drag of the upper face of the rectangle.
- Return type:
float
- flight_mech.aerodynamics.compute_linear_drag(x_array: ndarray, velocity_array: ndarray, rho: float, nu: float, method: Literal['blasius', 'polhausen', 'simulation'], return_array: bool = False)[source]#
- flight_mech.aerodynamics.compute_polhausen_linear_drag(x_array: ndarray, velocity_array: ndarray, rho: float, nu: float, return_array: bool = False)[source]#
Compute the linear drag using the Von-Karman Polhausen’s method.
- Parameters:
x_array (np.ndarray) – Array of x coordinates along the airfoil.
velocity_array (np.ndarray) – Array of external velocity along the airfoil.
rho (float) – Density of the fluid.
nu (float) – Kinematic viscosity of the fluid.
References
This method is explained in details in the “Aerodynamics for Engineering Students 6th edition” page 567.
https://univ-scholarvox-com.ezproxy.universite-paris-saclay.fr/book/88809524
- Returns:
Linear drag.
- Return type:
float