def test_static_temperature():
"""
This function tests the static_temperature() function
"""
stag_temp = 803.59
stat_temp = Stagnation.static_temperature(stag_temp, mach_number, gamma)
assert isclose(stat_temp, 800.0, rel_tol=1.0e-3)
def test_speed_of_sound():
"""
This function tests the speed_of_sound() function
"""
temp = 800.0
sos = Stagnation.speed_of_sound(gamma, temp, 28.014)
assert isclose(576.53, sos, rel_tol=1.0e-3)
def test_static_pressure():
"""
This function tests the static_pressure() function
"""
stag_pres = 6095032.0
stat_pres = Stagnation.static_pressure(stag_pres, mach_number, gamma)
assert isclose(stat_pres, 6000000.0, rel_tol=1.0e-3)
def test_pressure_based_mach():
"""
This function tests the pressure_based_mach() function
"""
stag_pressure = 6095032.0
stat_pressure = 6000000.0
mach = Stagnation.pressure_based_mach(stag_pressure, stat_pressure, gamma)
assert isclose(mach, 0.15, rel_tol=1.0e-3)
def test_temperature_based_mach():
"""
This function tests the temperature_based_mach() function
"""
stag_temp = 803.59
stat_temp = 800.0
mach = Stagnation.temperature_based_mach(stag_temp, stat_temp, gamma)
assert isclose(mach, 0.15, rel_tol=1.0e-2)
def test_mach_number():
"""
This function tests the mach_number() function
"""
temp = 800.0
velocity = 600.0
molar_mass = 28.014
mach = Stagnation.mach_number(gamma, temp, molar_mass, velocity)
assert isclose(1.04, mach, rel_tol=1.0e-2)
def test_press_exit_mach():
"""
This function tests the press_exit_mach() function
"""
entrance_mach = 0.25
exit_mach = 0.05
inlet_press = 6000000.0
exit_press = 6236000.0
remainder = Stagnation.press_exit_mach(exit_mach, entrance_mach, gamma,
inlet_press, exit_press)
assert isclose(remainder, -7.58682e-5, rel_tol=1.0e-3)
def test_temp_exit_mach():
"""
This function tests the temp_exit_mach() function
"""
entrance_mach = 0.19
exit_mach = 0.2151
inlet_temp = 800.0
exit_temp = 1000.0
remainder = Stagnation.temp_exit_mach(exit_mach, entrance_mach,
gamma, inlet_temp, exit_temp)
assert isclose(-9.00597e-5, remainder, rel_tol=1.0e-3)
def test_reactor_loop():
elec_power = 50000.0
species = 'nitrogen'
gas = Chemical(species)
heat_eff = 0.90
turb_eff = 0.90
comp_rat_guess = 1.18
comp_eff = 0.90
conv_eff = 0.25
inlet_stat_temp = 800.0 # Kelvins
inlet_stat_pres = 6000000.0 # Pascals
gas.calculate(T=inlet_stat_temp, P=inlet_stat_pres)
mw = gas.MW
gamma1 = gas.Cp / gas.Cvg
cp = gas.Cp
inlet_mach_number = 0.1
inlet_stag_temp = Stagnation.stagnation_temperature(inlet_stat_temp,
inlet_mach_number, gamma1)
inlet_stag_pres = Stagnation.stagnation_pressure(inlet_stat_pres,
inlet_mach_number, gamma1)
deltat = 50.0 # Kelvins
mdot = (elec_power / conv_eff) / (cp * deltat)
reac = ReactorLoop(heat_eff, turb_eff, species)
dicts = reac.performance(inlet_stag_temp, inlet_stag_pres, inlet_mach_number, inlet_stat_temp,
inlet_stat_pres, elec_power, comp_rat_guess, comp_eff,
conv_eff, mdot)
print('Compressor')
print(dicts[0])
print('Heat')
print(dicts[1])
print('Turbine')
print(dicts[2])
print('Rejection')
print(dicts[3])
def test_turbo_prop():
species = 'nitrogen'
gas = Chemical(species)
prop_eff = 0.98
prop_work = 200000.0
dif_eff = 0.95
diff_inlet_area = 0.0729
diff_outlet_area = 0.2
comp_ratio = 2.5
comp_eff = 0.9
heat_eff = 0.98
nozzle_eff = 0.95
turb_eff = 0.95
turb_work = 89286.33
nozzle_inlet_area = 0.462
nozzle_outlet_area = 0.23
temp = 81.05 # Kelvins
pres = 49300.0 # Pascals
gas.calculate(T=temp, P=pres)
density = gas.rho
gamma1 = gas.Cp / gas.Cvg
mw = gas.MW
sos = (gamma1 * ((1000.0 * 8.314) / mw) * temp) ** 0.5
velocity = 100.0 # m/s
mach = velocity / sos
mdot = density * velocity * diff_inlet_area # kg/s
stat_temp = Stagnation.static_temperature(temp, mach, gamma1)
stat_pres = Stagnation.static_pressure(pres, mach, gamma1)
jet = TurboProp(dif_eff, diff_inlet_area, diff_outlet_area, comp_ratio, comp_eff,
heat_eff, turb_eff, nozzle_eff, nozzle_inlet_area, nozzle_outlet_area,
prop_eff, species)
prop, dif, comp, heat, turb, noz = jet.performance(prop_work, temp, mdot, pres,
mach, stat_temp, stat_pres,
10000.0, turb_work)
assert isclose(prop['static_temperature'], 86.526, rel_tol=1.0e-3)
assert isclose(prop['static_pressure'], 22255.00, rel_tol=1.0e-3)
assert isclose(prop['stagnation_temperature'], 93.969, rel_tol=1.0e-3)
assert isclose(prop['stagnation_pressure'], 29707.25, rel_tol=1.0e-3)
assert isclose(prop['velocity'], 124.35, rel_tol=1.0e-3)
assert isclose(prop['mach_number'], 0.6558, rel_tol=1.0e-3)
assert isclose(prop['total_work'], 204081.63, rel_tol= 1.0e-3)
assert isclose(dif['static_temperature'], 92.608, rel_tol=1.0e-3)
assert isclose(dif['stagnation_pressure'], 29297.508, rel_tol=1.0e-3)
assert isclose(dif['static_pressure'], 28228.34, rel_tol=1.0e-3)
assert isclose(dif['stagnation_temperature'], 93.597, rel_tol=1.0e-3)
assert isclose(dif['velocity'], 45.326, rel_tol=1.0e-3)
assert isclose(dif['mach_number'], 0.2310, rel_tol=1.0e-3)
assert isclose(dif['density'], 1.6773, rel_tol=1.0e-3)
assert isclose(comp['static_temperature'], 122.88, rel_tol=1.0e-3)
assert isclose(comp['stagnation_pressure'], 73243.77, rel_tol=1.0e-3)
assert isclose(comp['static_pressure'], 69531.38, rel_tol=1.0e-3)
assert isclose(comp['stagnation_temperature'], 124.72, rel_tol=1.0e-3)
assert isclose(comp['velocity'], 61.82, rel_tol=1.0e-3)
assert isclose(comp['mach_number'], 0.2736, rel_tol=1.0e-3)
assert isclose(comp['work'], 546239.28, rel_tol=1.0e-3)
assert isclose(heat['static_temperature'], 123.49, rel_tol=1.0e-3)
assert isclose(heat['stagnation_pressure'], 73224.28, rel_tol=1.0e-3)
assert isclose(heat['static_pressure'], 69509.28, rel_tol=1.0e-3)
assert isclose(heat['stagnation_temperature'], 125.35, rel_tol=1.0e-3)
assert isclose(heat['velocity'], 62.16, rel_tol=1.0e-3)
assert isclose(heat['mach_number'], 0.2744, rel_tol=1.0e-3)
assert isclose(heat['power'], 10204.08, rel_tol=1.0e-3)
assert isclose(turb['static_temperature'], 117.73, rel_tol=1.0e-3)
assert isclose(turb['stagnation_pressure'], 61199.27, rel_tol=1.0e-3)
assert isclose(turb['static_pressure'], 58251.17, rel_tol=1.0e-3)
assert isclose(turb['stagnation_temperature'], 119.40, rel_tol=1.0e-3)
assert isclose(turb['velocity'], 58.94, rel_tol=1.0e-3)
assert isclose(turb['mach_number'], 0.2665, rel_tol=1.0e-3)
assert isclose(turb['extracted_work'], 93985.61, rel_tol=1.0e-3)
assert isclose(noz['static_temperature'], 112.57, rel_tol=1.0e-3)
assert isclose(noz['stagnation_pressure'], 61049.38, rel_tol=1.0e-3)
assert isclose(noz['static_pressure'], 49795.29, rel_tol=1.0e-3)
assert isclose(noz['stagnation_temperature'], 119.31, rel_tol=1.0e-3)
assert isclose(noz['velocity'], 118.40, rel_tol=1.0e-3)
assert isclose(noz['mach_number'], 0.5474, rel_tol=1.0e-3)
assert isclose(noz['density'], 0.5583, rel_tol=1.0e-3)