fastga.models.aerodynamics.external.propeller_code.propeller_core module
Computation of propeller aero properties.
- class fastga.models.aerodynamics.external.propeller_code.propeller_core.PropellerCoreModule(**kwargs)[source]
Bases:
openmdao.core.explicitcomponent.ExplicitComponentCore component for the computation of the propeller performance.
Compressibility correction are taken from [HJimenezEchavarria+22] for subsonic corrections. Reynolds effects correction are taken from yamauchi:1983.
Store some bound methods so we can detect runtime overrides.
- compute_extreme_pitch(inputs, v_inf)[source]
For a given flight speed computes the min and max possible value of theta at .75 r/R.
- compute_pitch_performance(inputs, theta_75, v_inf, altitude, omega, radius, alpha_list, cl_list, cd_list)[source]
This function calculates the thrust, efficiency and power at a given flight speed, altitude h and propeller angular speed.
- Parameters
inputs – structure of data relative to the blade geometry available from setup
theta_75 – pitch defined at r = 0.75*R radial position [deg].
v_inf – flight speeds [m/s].
altitude – flight altitude [m].
omega – angular velocity of the propeller [RPM].
radius – array of radius of discretized blade elements [m].
alpha_list – angle of attack list for aerodynamic coefficient of profile at
discretized blade element [deg]. :param cl_list: cl list for aerodynamic coefficient of profile at discretized blade element [-]. :param cd_list: cd list for aerodynamic coefficient of profile at discretized blade element [-].
- Returns
thrust [N], eta (efficiency) [-] and power [W].
- static bem_theory(speed_vect: numpy.array, radius: float, chord: float, blades_number: float, sweep: float, omega: float, v_inf: float, theta: float, alpha_element: numpy.array, cl_element: numpy.array, cd_element: numpy.array, atm: stdatm.atmosphere.Atmosphere, reference_reynolds: float)[source]
The core of the Propeller code. Given the geometry of a propeller element, its aerodynamic polars, flight conditions and axial/tangential velocities it computes the thrust and the torque produced using force and momentum with BEM theory.
- Parameters
speed_vect – the vector of axial and tangential induced speed in m/s
radius – radius position of the element center [m]
chord – chord at the center of element [m]
blades_number – number of blades [-]
sweep – sweep angle [deg.]
omega – angular speed of propeller [rad/sec]
v_inf – flight speed [m/s]
theta – profile angle relative to aircraft airflow v_inf [deg.]
alpha_element – reference angle vector for element polars [deg.]
cl_element – cl vector for element [-]
cd_element – cd vector for element [-]
atm – atmosphere properties
reference_reynolds – Reynolds number at which the aerodynamic properties were computed
- Returns
The calculated dT/(rho*dr) and dQ/(rho*dr) increments with BEM method.
- static disk_theory(speed_vect: numpy.array, radius: float, radius_min: float, radius_max: float, blades_number: float, sweep: float, omega: float, v_inf: float)[source]
The core of the Propeller code. Given the geometry of a propeller element, its aerodynamic polars, flight conditions and axial/tangential velocities it computes the thrust and the torque produced using force and momentum with disk theory.
- Parameters
speed_vect – the vector of axial and tangential induced speed in m/s
radius – radius position of the element center [m]
radius_min – Hub radius [m]
radius_max – Max radius [m]
blades_number – number of blades [-]
sweep – sweep angle [deg.]
omega – angular speed of propeller [rad/sec]
v_inf – flight speed [m/s]
- Returns
The calculated dT/(rho*dr) and dQ/(rho*dr) increments with disk theory method.
- delta(speed_vect: numpy.array, radius: float, radius_min: float, radius_max: float, chord: float, blades_number: float, sweep: float, omega: float, v_inf: float, theta: float, alpha_element: numpy.array, cl_element: numpy.array, cd_element: numpy.array, atm: stdatm.atmosphere.Atmosphere, reference_reynolds: float)[source]
The core of the Propeller code. Given the geometry of a propeller element, its aerodynamic polars, flight conditions and axial/tangential velocities it computes the thrust and the torque produced using force and momentum with disk theory.
- Parameters
speed_vect – the vector of axial and tangential induced speed in m/s
radius – radius position of the element center [m]
radius_min – Hub radius [m]
radius_max – Max radius [m]
chord – chord at the center of element [m]
blades_number – number of blades [-]
sweep – sweep angle [deg.]
omega – angular speed of propeller [rad/sec]
v_inf – flight speed [m/s]
theta – profile angle relative to aircraft airflow v_inf [DEG]
alpha_element – reference angle vector for element polars [DEG]
cl_element – cl vector for element [-]
cd_element – cd vector for element [-]
atm – atmosphere properties
reference_reynolds – Reynolds number at which the aerodynamic properties were computed
- Returns
The difference between BEM dual methods for dT/(rho*dr) and dQ/ increments.