from common import Atmosphere
from test.test_library import is_close
h_0 = Atmosphere(0)
h_40k = Atmosphere(40000)
out = list()
out.append((is_close(h_0.air_density(), 0.002379)))
out.append(is_close(h_40k.air_density(), 0.0005848))
out.append((is_close(h_0.pressure(), 2118.145)))
out.append(is_close(h_40k.pressure(), 391.234))
out.append((is_close(h_0.speed_of_sound(), 1116.462)))
out.append(is_close(h_40k.speed_of_sound(), 967.723))
out.append((is_close(h_0.viscosity(), 3.737e-07)))
out.append(is_close(h_40k.viscosity(), 2.967e-07))
if any(out):
print("atmosphere test passed!")
else:
print("atmosphere test failed")
from common import Gravity
from test.test_library import is_close
h_0 = Gravity(0)
h_40k = Gravity(40000)
out = list()
out.append((is_close(h_0.gravity(), 32.14894)))
out.append(is_close(h_40k.gravity(), 32.026389))
if any(out):
print("earth test passed!")
else:
print("earth test failed")
from numpy import pi mach = 0.3 altitude = 10000 c_l_alpha = 2 * pi x_ref = 5 ar = 5 sweep_le = 30 taper = 0.5 q_e = dynamic_pressure(mach, altitude) c_f = friction_coefficient(mach, altitude, x_ref) re = reynolds_number(mach, altitude, x_ref) c_l_alpha_w = polhamus(c_l_alpha, ar, mach, taper, sweep_le) out = list() out.append((is_close(q_e, 91.83224))) out.append(is_close(c_f, 0.003111)) out.append(is_close(re, 8038249.384)) out.append(is_close(c_l_alpha_w, 4.2811)) mach = 0.6 altitude = 30000 ar = 3 q_e = dynamic_pressure(mach, altitude) c_f = friction_coefficient(mach, altitude, x_ref) re = reynolds_number(mach, altitude, x_ref) c_l_alpha_w = polhamus(c_l_alpha, ar, mach, taper, sweep_le) out.append((is_close(q_e, 158.89079))) out.append(is_close(c_f, 0.00307937))
from src.modeling.trapezoidal_wing import mac, root_chord, span, sweep_x, x_mac, y_chord, y_mac
from test.test_library import is_close
ar = 5
s = 10
sweep_le = 30
taper = 0.5
c_bar = mac(ar, s, taper)
cr = root_chord(ar, s, taper)
b = span(ar, s)
sweep = sweep_x(ar, taper, sweep_le, 0.5)
y = y_mac(ar, s, taper)
x = x_mac(3, sweep_le)
c = y_chord(0.25, cr, b, taper)
out = list()
out.append((is_close(c_bar, 1.46659)))
out.append(is_close(b, 7.071067))
out.append(is_close(cr, 1.8856))
out.append(is_close(c, 1.81895))
out.append(is_close(x, 1.73205))
out.append(is_close(y, 1.5713))
out.append(is_close(sweep, 23.942))
if any(out):
print("trapezoidal wing test passed!")
else:
print("trapezoidal wing test failed")
'name': 'elevator_l',
'cf_c': 0.3,
'b_1': -0.999,
'b_2': -0.01,
},
'control_2': {
'name': 'elevator_r',
'cf_c': 0.3,
'b_1': 0.01,
'b_2': 0.999,
},
}
cg = [40, 0, 1]
mach = 0.5
c_l = c_f_m_flap(ht, ht['control_1'], mach, cg)
c_r = c_f_m_flap(ht, ht['control_2'], mach, cg)
c = c_l + c_r
out = list()
out.append((is_close(c_l[3], 6.1968)))
out.append((is_close(c_r[3], -6.1968)))
out.append((is_close(c[1], 0)))
out.append((is_close(c[2], -1.0188)))
out.append((is_close(c[4], -49.36)))
if any(out):
print("flap test passed!")
else:
print("flap test failed")
from rotations import angular_rate_rotation, body_to_wind, eci_to_ned, ned_to_body
from numpy import pi
from test.test_library import is_close
e2b = angular_rate_rotation(5 * pi/180, 5 * pi/180)
b2w = body_to_wind(5 * pi/180, 5 * pi/180)
e2n = eci_to_ned(5 * pi/180, 5 * pi/180)
n2b = ned_to_body(5 * pi/180, 5 * pi/180, 5 * pi/180)
out = list()
out.append(is_close(e2b[0, 0], 1))
out.append(is_close(e2b[1, 1], 0.99619))
out.append(is_close(e2b[2, 2], 1))
out.append(is_close(b2w[0, 0], 0.9924))
out.append(is_close(b2w[1, 1], 0.99619))
out.append(is_close(b2w[2, 2], 0.99619))
out.append(is_close(e2n[0, 0], 0.99619))
out.append(is_close(e2n[1, 1], 0.99619))
out.append(is_close(e2n[2, 2], 0.9924))
out.append(is_close(n2b[0, 0], 0.9924))
out.append(is_close(n2b[1, 1], 0.99306))
out.append(is_close(n2b[2, 2], 0.9924))
if any(out):
print("rotation test passed!")
else:
print("rotation test failed")
'buttline': -30, # [ft]
'thrust_angle': 5, # [deg]
'toe_angle': -2, # [deg]
'diameter': 4, # [ft]
'rpm_max': 10000, # [rpm]
'pitch': 20 # [deg]
},
}
cg = [43, 0, 2]
throttle = [1, 1]
x = [100, 30000]
p = Propulsion(propulsion, x, throttle, cg)
cfm = p.thrust_f_m()
out = list()
out.append((is_close(cfm[0], 4780.1585)))
out.append((is_close(cfm[4], 10220.1982)))
out.append((is_close(cfm[3], 0)))
throttle = [0.5, 0.5]
x = [200, 0]
p = Propulsion(propulsion, x, throttle, cg)
cfm = p.thrust_f_m()
out.append((is_close(cfm[0], 713.781)))
out.append((is_close(cfm[4], 1526.0972)))
out.append((is_close(cfm[3], 0)))
propulsion = {
'n_engines': 1,
'engine_1': {
'type': 'jet',
from Gravity import Gravity from test.test_library import is_close h_0 = Gravity(0) h_40k = Gravity(40000) out = list() out.append((is_close(h_0.gravity(), 32.14894))) out.append(is_close(h_40k.gravity(), 32.026389)) h_0 = Gravity(0).gravity(planet='mars') h_40k = Gravity(40000).gravity(planet='mars') out = list() out.append((is_close(h_0, 12.17927))) out.append(is_close(h_40k, 12.09213)) h_0 = Gravity(0).gravity(planet='jupiter') h_40k = Gravity(40000).gravity(planet='jupiter') out = list() out.append((is_close(h_0, 88.82685))) out.append(is_close(h_40k, 88.79586)) h_0 = Gravity(0).gravity(planet='mercury') h_40k = Gravity(40000).gravity(planet='mercury') out = list() out.append((is_close(h_0, 12.08413))) out.append(is_close(h_40k, 11.96425))
vertical = {
'planform': 50, # [ft^2]
}
fuselage = {
'width': 10, # [ft]
'height': 10, # [ft]
}
mach = 0.3
altitude = 20000
w = LiftingSurface(wing)
c_l_a = w.c_l_alpha_wing(mach)
de_da = w.d_epsilon_d_alpha(horizontal, mach)
ac = w.aerodynamic_center()
cd0 = w.parasite_drag(mach, altitude)
ds_db_v = w.d_sigma_d_beta_vt(vertical, fuselage)
ds_db_h = w.d_sigma_d_beta_ht(horizontal, fuselage)
out = list()
out.append((is_close(c_l_a, 4.23295)))
out.append((is_close(de_da, 0.27033)))
out.append((is_close(ac, 41.2388)))
out.append((is_close(cd0, 0.00766999)))
out.append((is_close(ds_db_v, 0.95375)))
out.append((is_close(ds_db_h, 1.0715)))
if any(out):
print("lifting surface test passed!")
else:
print("lifting surface test failed")