def _load(path, atmosphere=std_atm_earth()):
data = {}
with open(path) as f:
data = json.load(f)
engine = data.get('engine', {})
engine_name = engine.get('name', None)
# If name is specified, look for it in the engine database
# Then fall-back on database values if they're not given in the plane.json file
engine_in_db = engine_db.get(engine_name,
{}) if engine_name is not None else {}
T_a_sl = engine.get('thrust', engine_in_db.get('thrust', None))
cost_engines = engine.get('cost', engine_in_db.get('cost', None))
engine_count = data.get('engine_count', 1)
if T_a_sl is not None: T_a_sl *= engine_count
if cost_engines is not None: cost_engines *= engine_count
weight = data.get('weight', {'struct': 0, 'fuel': 0, 'payload': 0})
W_struct = weight.get('struct', 0)
W_fuel = weight.get('fuel', 0)
W_payload = weight.get('payload', 0)
W_engines = engine.get('weight', engine_in_db.get('weight',
0)) * engine_count
cost_struct = data.get('cost', None)
if (cost_struct is not None) and (cost_engines is not None):
cost_struct -= cost_engines
plane = Plane(
data.get('Cd_0', None),
data.get('e_w', None),
data.get('S', None),
data.get('b', None),
data.get('Cl_max', None),
data.get('Lam', None),
data.get('tc_max', None),
W_struct,
W_fuel,
W_engines,
W_payload,
engine.get('cj', engine_in_db.get('cj', None)),
T_a_sl,
data.get('n_struct', None),
atmosphere,
)
plane._description = data.get('description', None)
plane._cost_engines = cost_engines
plane._cost_struct = cost_struct
return plane
velocities)
plt.cla()
plt.clf()
plt.plot(velocities, P_a_0, '--b', label='P_a @ h = 0m')
plt.plot(velocities, P_r_0, '-b', label='P_r @ h = 0m')
plt.plot(velocities, P_a_45, '--r', label='P_a @ h = 4500m')
plt.plot(velocities, P_r_45, '-r', label='P_r @ h = 4500m')
plt.title('Power Available and Power Required for the F-117')
plt.xlabel('Velocity, V [m/s]')
plt.ylabel('Power [W]')
plt.legend(loc='upper right')
plt.show()
if __name__ == '__main__':
from haydens_code.atmosphere import std_atm_earth
from haydens_code.plane import Plane
# Initialize atmosphere object
atm = std_atm_earth()
# Initialize F-117 Warthog plane object
plane = Plane(0.042, None, 0.84, 84.8 / 13.2, 13.2, 1.2, None, None,
187000, 0.0, None, 96000, atm)
# plane = Plane(187000, 13.2, 84.8/13.2, 0.042, 0.84, 1.2, 96000)
QUESTION_2()
QUESTION_3()
# tc_max=0.11,
# W_0=88100,
# W_fuel=33200,
# cj=0.60,
# T_a_sl=32500,
# atmosphere=std_atm_earth()
# )
# Initialize MD-11 plane object
plane = Plane(Cd_0=0.018,
Em=None,
e=0.85,
chord=339 / 51.8,
span=51.8,
Cl_max=1.4,
Lam=35.0,
tc_max=0.12,
W_0=2710000,
W_fuel=None,
cj=None,
T_a_sl=800000,
atmosphere=std_atm_earth())
"""QUESTION 1 PLOT"""
plane.set_altitude(0) # meters
T_a = plane.jet_thrust_available() # N
V_limits = plane.speed_min_max(T_a) # m/s
V_range = np.arange(V_limits[0, 0], V_limits[1, 0] + 5, 5)
Cd_inc = plane.Cd(plane.Cd_i(plane.Cl(V_range)))
Cd_com = Cd_inc + plane.Cd_c(plane.Cl(V_range), V_range)
D_inc = plane.drag(Cd_inc, V_range) / 1000
D_com = plane.drag(Cd_com, V_range) / 1000
import sys
sys.path.append('..')
if __name__ == '__main__':
from haydens_code.atmosphere import std_atm_earth
from haydens_code.plane import Plane
# Initialize The Global Flyer plane object
plane = Plane(
Cd_0=0.016,
Em=None,
e=0.94,
chord=37.2 / 34.8,# MAC
span=34.8,
Cl_max=1.2,
Lam=None,
tc_max=None,
W_0=98000,
W_1=14900,
cj=0.42,
T_a_sl=10200,
atmosphere=std_atm_earth()
)
plane.set_altitude_range(500, 10000, 100)
drag = plane.drag(plane.Cd(plane.Cd_i(plane.Cl(80))), 80)
t_a = plane.jet_thrust_available()
R_C = 80*(t_a - drag)/98000
print(R_C)
plane.set_altitude(10000)
import sys
sys.path.append('..')
if __name__ == '__main__':
from haydens_code.atmosphere import std_atm_earth
from haydens_code.plane import Plane
# Initialize atmosphere object
atm = std_atm_earth()
# Initialize B-2 Spirit plane object
plane = Plane(1420000, 52.4, 9.1, 0.0090, 0.92, 1.22)
# Generate data at requested altitudes
altitudes = []
speed_const_Cl = []
speed_stall = []
drag_const_Cl = []
drag_210 = []
for i in range(0, 20001, 500):
plane.set_altitude(i)
altitudes.append(i)
density = atm.density_at(i)
speed_stall.append(plane.speed_stall())
speed = plane.speed(plane.Cl_min_drag)
speed_const_Cl.append(speed)
Cd_min = plane.Cd(plane.Cd_i(plane.Cl_min_drag))
drag_const_Cl.append(plane.drag(Cd_min, speed))
import numpy as np
import matplotlib.pyplot as plt
if __name__ == '__main__':
from haydens_code.atmosphere import std_atm_earth
from haydens_code.plane import Plane
# Initialize Boeing 777-200 plane object
plane = Plane(
Cd_0=0.020,
Em=None,
e=0.93,
chord=423 / 61, # MAC
span=61,
Cl_max=2.3,
Lam=31.6,
tc_max=0.13,
W_0=2380000,
W_1=None,
cj=None,
T_a_sl=342000 * 2,
atmosphere=std_atm_earth())
"""QUESTION 1 and 2 PLOTS ---------------------------------------------------------------------------------------"""
# FOR 0m --------------------------------------------------------------------------------------------------------
# compute velocity range
plane.set_altitude(0) # meters
T_a = plane.jet_thrust_available() # N
V_limits = plane.speed_min_max(T_a) # m/s
V_range = np.arange(V_limits[0, 0], V_limits[1, 0] + 5, 5)
# compute drag
Cd_inc = plane.Cd(plane.Cd_i(plane.Cl(V_range)))
if __name__ == '__main__':
from haydens_code.atmosphere import std_atm_earth
from haydens_code.plane import Plane
q3 = Plane(
Cd_0=0.020,
Em=None,
e=0.9,
chord=1.0, # MAC
span=8.0,
Cl_max=None,
Lam=None,
tc_max=None,
W_0=1.0,
W_1=None,
cj=None,
T_a_sl=0.2,
n_struct=None,
atmosphere=std_atm_earth(),
)
print(q3.Cd_0)
print(q3.AR)
print(q3.e_w)
print(q3.T_a_sl/q3.W_0)
print('')
print('n_aero: {}'.format(q3.n_aero))
print('')
q4 = Plane(
Cd_0=0.020,
import sys
sys.path.append('..')
if __name__ == '__main__':
from haydens_code.atmosphere import std_atm_earth
from haydens_code.plane import Plane
# Initialize atmosphere object
atm = std_atm_earth()
# Initialize A-10 Warthog plane object
plane = Plane(145000, 17.6, 2.676, 0.032, 0.87, 1.2, 80000)
"""QUESTION 1 - PART A"""
altitude = 11500 # m
plane.set_altitude(altitude)
density = atm.density_at(altitude)
thrust_avail = plane.jet_thrust_available()
# Generate data at requested velocities
speeds = []
lift_coeffs = []
drag_coeffs = []
drags = []
for speed in range(20, 301, 5):
Cl = plane.Cl(speed)
Cd = plane.Cd(plane.Cd_i(plane.Cl(speed)))
drag = plane.drag(Cd, speed)
speeds.append(speed)
lift_coeffs.append(Cl)
drag_coeffs.append(Cd)