aircraft

class aircraft.Aircraft(name: str, version: str, settings: pyNA.src.settings.Settings)[source]

Bases: object

Aircraft class containing vehicle constants and aerodynamics data.

B_fan: int
M_d_fan: float
RSS_fan: float
TS_lower: float
TS_upper: float
V_fan: int
__init__(name: str, version: str, settings: pyNA.src.settings.Settings) → None[source]

Initialize Aircraft class.

Parameters

  • name (str) – aircraft name

  • version (str) – aircraft version

  • settings (Settings) – pyna settings

Returns

None

af_N_mg: float
af_N_ng: float
af_S_f: float
af_S_h: float
af_S_v: float
af_S_w: float
af_b_f: float
af_b_h: float
af_b_v: float
af_b_w: float
af_clean_h: bool
af_clean_v: bool
af_clean_w: bool
af_d_mg: float
af_d_ng: float
af_delta_wing: bool
af_l_mg: float
af_l_ng: float
af_n_mg: float
af_n_ng: float
af_s: int
alpha_0: float
c_l_max: float
comp_lst: list
gamma_rot: float
static generate_aerodeck_from_csv(filename_c_l: str, filename_c_d: str, savename_c_l: str = None, savename_cd: str = None) → None[source]

Generate a CL-CD aerodynamics deck from a .csv data file.

Parameters

  • filename_c_l (str) – File name with c_l data as function of alpha, theta_flap, theta_slat

  • filename_cd (str) – File name with cd data as function of alpha, theta_flap, theta_slat

  • savename_c_l (str) – Save file name of c_l-aerodynamics deck

  • savename_cd (str) – Save file name of c_d-aerodynamics deck

Returns

None

inc_F_n: float
k_rot: float
load_aerodynamics(settings: pyNA.src.settings.Settings) → None[source]

Load aerodynamic data from aerodynamics deck.

Parameters

settings (Settings) – pyNA settings

Returns

None

mtow: float
mu_r: float
n_eng: int
set_aircraft_parameters(mtow: numpy.float64, n_eng: numpy.int64, comp_lst: list, af_S_h: numpy.float64, af_S_v: numpy.float64, af_S_w: numpy.float64, af_b_f: numpy.float64, af_b_h: numpy.float64, af_b_v: numpy.float64, af_b_w: numpy.float64, theta_flaps: numpy.float64, theta_slats: numpy.float64, af_S_f: numpy.float64, af_s: numpy.int64, af_d_mg: numpy.float64, af_d_ng: numpy.float64, af_l_mg: numpy.float64, af_l_ng: numpy.float64, af_n_mg: numpy.float64, af_n_ng: numpy.float64, af_N_mg: numpy.float64, af_N_ng: numpy.float64, mu_r: numpy.float64, B_fan: numpy.int64, V_fan: numpy.int64, RSS_fan: numpy.float64, M_d_fan: numpy.float64, inc_F_n: numpy.float64, TS_lower: numpy.float64, TS_upper: numpy.float64, af_clean_w: bool, af_clean_h: bool, af_clean_v: bool, af_delta_wing: bool, alpha_0: numpy.float64, k_rot: numpy.float64, v_max: numpy.float64, z_max: numpy.float64, gamma_rot: numpy.float64) → None[source]

Set the aircraft parameters in the aircraft class.

Parameters

  • mtow (np.float64) – Max. take-off weight [kg]

  • n_eng (np.int64) – Number of engines installed on the aircraft [-]

  • comp_lst (list) – List of airframe components to include [-]

  • af_S_h (np.float64) – Horizontal tail area [m2]

  • af_S_v (np.float64) – Vertical tail area [m2]

  • af_S_w (np.float64) – Wing area [m2]

  • af_b_f (np.float64) – Flap span [m]

  • af_b_h (np.float64) – Horizontal tail span [m]

  • af_b_v (np.float64) – Vertical tail span [m]

  • af_b_w (np.float64) – Wing span [m]

  • theta_flaps (np.float64) – Flap deflection angle [deg]

  • theta_slats (np.float64) – Slat deflection angle [deg]

  • af_S_f (np.float64) – Flap area [m2]

  • af_s (np.int64) – Number of slots for trailing-edge flaps (min. is 1) [-]

  • af_d_mg (np.float64) – Tire diameter of main landing gear [m]

  • af_d_ng (np.float64) – Tire diameter of nose landing gear [m]

  • af_l_mg (np.float64) – Main landing-gear strut length [m]

  • af_l_ng (np.float64) – Nose landing-gear strut length [m]

  • af_n_mg (np.int64) – Number of wheels per main landing gear [-]

  • af_n_ng (np.int64) – Number of wheels per nose landing gear [-]

  • af_N_mg (np.int64) – Number of main landing gear [-]

  • af_N_ng (np.int64) – Number of nose landing gear [-]

  • mu_r (np.float64) – Rolling resistance coefficient [-]

  • B_fan (np.int64) – Number of fan blades [-]

  • V_fan (np.int64) – Number of fan vanes [-]

  • RSS_fan (np.float64) – Rotor-stator spacing [%]

  • M_d_fan (np.float64) – Relative tip Mach number of fan at design [-]

  • inc_F_n (np.float64) – Thrust inclination angle [deg]

  • TS_lower (np.float64) – Min. power setting [-]

  • TS_upper (np.float64) – Max. power setting [-]

  • af_clean_w (bool) – Flag for clean wing configuration [-]

  • af_clean_h (bool) – Flag for clean horizontal tail configuration [-]

  • af_clean_v (bool) – Flag for clean vertical tail configuration [-]

  • af_delta_wing (bool) – Flag for delta wing configuration [-]

  • alpha_0 (np.float64) – Wing mounting angle [deg]

  • k_rot (np.float64) – Rotation coefficient (v_rot/v_stall) [-]

  • v_max (np.float64) – Maximum climb-out velocity [m/s]

  • z_max (np.float64) – Maximum climb-out altitude [m]

  • gamma_rot (np.float64) – Initial climb angle [deg]

Returns

None

theta_flaps: float
theta_slats: float
v_max: float
z_max: float