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
plt.plot(V_range, D_inc, '-r', label='Drag (incompressible)')
plt.plot(V_range, D_com, '--r', label='Drag (compressible)')
plt.plot(V_range, [T_a / 1000 for i in range(V_range.shape[0])],
'-b',
label='Thrust Available')
plt.xlim(V_range.min() - 10, V_range.max() + 10)
plt.ylim(D_inc.min() - 50, D_inc.max() + 10)
plt.title('Drag vs Velocity for MD-11 at Sea Level')
plt.xlabel('Velocity [m/s]')
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)
print(plane.jet_thrust_available())
print(plane.speed_min_max(plane.jet_thrust_available()))
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)))
Cd_com = Cd_inc + plane.Cd_c(plane.Cl(V_range), V_range)
D_inc = plane.drag(Cd_inc, V_range)
D_com = plane.drag(Cd_com, V_range)
# compute R/C
RC_inc = plane.rate_of_climb(D_inc, V_range)
RC_com = plane.rate_of_climb(D_com, V_range)
print('% Difference (R/C max @ 0km), Incompressible and Compressible: {}'.
format(100 * (RC_inc.max() - RC_com.max()) / RC_inc.max()))
# plot
plt.plot(V_range / plane.sound_speed,
RC_inc,
'-r',
label='R/C (incompressible), 0m')
plt.plot(V_range / plane.sound_speed,
RC_com,
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))
speed = 210 # m/s
Cd = plane.Cd(plane.Cd_i(plane.Cl(speed)))
drag_210.append(plane.drag(Cd, speed))
# Reformat as Strings
alt_str = ['%d' % i for i in altitudes]
v_const_Cl_str = ['%.1f' % i for i in speed_const_Cl]
d_const_Cl_str = ['%.2f' % (i / 1000.0) for i in drag_const_Cl]
d_210_str = ['%.2f' % (i / 1000.0) for i in drag_210]
data = [[a, v_Cl, d_Cl, d_210] for a, v_Cl, d_Cl, d_210 in zip(
alt_str, v_const_Cl_str, d_const_Cl_str, d_210_str)]
# Start working with matplotlib to view data in a table
from matplotlib import pyplot as plt
from matplotlib.font_manager import FontProperties
# 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)
drags.append(drag)
# Start working with matplotlib to view data
from matplotlib import pyplot as plt
from matplotlib.font_manager import FontProperties
plt.plot(speeds, drags, '-r', label='T_r')
# plt.title('Drag vs. Velocity at 500m')
plt.xlabel('Velocity [m/s]')