print_payloadrange_jet = False print_payloadrange_tbp = True weight_fractions = False ## INPUTS AND CONSTANTS # fuel efficiency chosen_fuel_energy_density = energy_density_kerosene fuel_efficiency_factor = energy_density_kerosene/chosen_fuel_energy_density # Flight parameters s_landing = 1400 #[m] altitude = 7600 V_landing = 48.93 #[m/s] maximum landing speed that is allowed on a runway of 1400 m this is set for all aircraft # Atmospherical parameters at cruise altitude temperature, pressure, rho, speed_of_sound = atmosphere_calc(altitude, temperature0, temperature_gradient, g, R, gamma) # Initial jet and tbp aircraft parameters C_fe = 0.003 S = 1 S_wet = 5 * S c = 6.88 #[m/s] # Other jet parameters A_jet = 10 e_jet = 0.8 M_cruise_jet = 0.8 V_cruise_jet = M_cruise_jet*speed_of_sound # [m/s] S_jet = 61 TOP_jet = 6698 C_L_cruise_jet = 0.4
import parameters as p
import numpy as np
import matplotlib.pyplot as plt
from atmosphere import atmosphere_calc
# Atmosphere Input Parameters
t0 = p.temperature0
t_gradient = p.temperature_gradient
atR = p.R
atgamma = p.gamma
g = p.g
rho0 = p.rho0
altitude1 = 8000
temperature, pressure, rho, speed_of_sound = atmosphere_calc(
altitude1, t0, t_gradient, g, atR, atgamma)
rho = rho * rho0
# Aircraft Input Parameters
S = p.S
W = p.MTOW
A = p.A
e = p.e
CD0 = p.Cd0
CLmaxprofile = 1.5
CLmaxto = (p.C_L_max_TO + CLmaxprofile) / 2 * 0.85
CLmaxld = (p.C_L_max_land + CLmaxprofile) / 2 * 0.85
CLmaxclean = CLmaxprofile * 0.85
#CDcruise = CD0 + CLcruise**2/(np.pi*A*e)
V_S = np.sqrt((2 * W) / (rho * CLmaxclean * S))
import parameters as p
import numpy as np
import matplotlib.pyplot as plt
from atmosphere import atmosphere_calc
# Runway Input Parameters
g = p.g
rho0 = p.rho0
mu = 0.02
altrange = np.linspace(0, 1500, 100)
dist_TO = []
for altitude in altrange:
temperature, pressure, rho, speed_of_sound = atmosphere_calc(
altitude, p.temperature0, p.temperature_gradient, p.g, p.R, p.gamma)
rho = 1.225 * rho
pressure = 101325 * pressure
# Aircraft Input Parameters
S = 61
CL = 1.6
CD0 = 0.02
CD = CD0 + CL**2 / (np.pi * p.A * p.e)
P = 3.689e6
W = 223668
# Take-Off Input Parameters
V_stall = np.sqrt((W / S) * (2 / rho) * (1 / CL))
gamma = 4 * (np.pi / 180)
n_rotation = 1.15