本文整理汇总了Python中SUAVE.Core.Data.mdot方法的典型用法代码示例。如果您正苦于以下问题：Python Data.mdot方法的具体用法？Python Data.mdot怎么用？Python Data.mdot使用的例子？那么, 这里精选的方法代码示例或许可以为您提供帮助。您也可以进一步了解该方法所在类SUAVE.Core.Data的用法示例。
在下文中一共展示了Data.mdot方法的4个代码示例，这些例子默认根据受欢迎程度排序。您可以为喜欢或者感觉有用的代码点赞，您的评价将有助于系统推荐出更棒的Python代码示例。
示例1: energy_network
# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import mdot [as 别名]
#.........这里部分代码省略.........
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
# Component 10 - Thrust
# instantiate
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='thrust'
# setup
thrust.total_design = 42383.01818423
# add to network
turbofan.thrust = thrust
numerics = Data()
eta=1.0
#size the turbofan
turbofan_sizing(turbofan,0.8,10000.0)
print("Design thrust ",turbofan.design_thrust)
print("Sealevel static thrust ",turbofan.sealevel_static_thrust)
results_design = turbofan(state_sizing)
results_off_design = turbofan(state_off_design)
F = results_design.thrust_force_vector
mdot = results_design.vehicle_mass_rate
F_off_design = results_off_design.thrust_force_vector
mdot_off_design = results_off_design.vehicle_mass_rate
#Test the model
#Specify the expected values
expected = Data()
expected.thrust = 42360.88505056
expected.mdot = 0.76399257
#error data function
error = Data()
error.thrust_error = (F[0][0] - expected.thrust)/expected.thrust
error.mdot_error = (mdot[0][0]-expected.mdot)/expected.mdot
print(error)
for k,v in list(error.items()):
assert(np.abs(v)<1e-6)
return示例2: energy_network
# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import mdot [as 别名]
#.........这里部分代码省略.........
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
ramjet.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 1.0
inlet_nozzle.pressure_ratio = 1.0
inlet_nozzle.compressibility_effects = True
# add to network
ramjet.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 1.0
combustor.turbine_inlet_temperature = 2400.
combustor.pressure_ratio = 1.0
combustor.area_ratio = 2.0
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
combustor.rayleigh_analyses = True
# add to network
ramjet.append(combustor)
# ------------------------------------------------------------------
# Component 4 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Supersonic_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 1.0
nozzle.pressure_ratio = 1.0
# add to network
ramjet.append(nozzle)
# ------------------------------------------------------------------
# Component 5 - Thrust
# instantiate
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='thrust'
# setup
thrust.total_design = ramjet.number_of_engines*169370.4652 * Units.N
# add to network
ramjet.thrust = thrust
#size the ramjet
ramjet_sizing(ramjet,2.5,10000.0)
print "Design thrust :",ramjet.design_thrust
print "Sealevel static thrust :",ramjet.sealevel_static_thrust
results_design = ramjet(state_sizing)
results_off_design = ramjet(state_off_design)
F = results_design.thrust_force_vector
mdot = results_design.vehicle_mass_rate
Isp = results_design.specific_impulse
F_off_design = results_off_design.thrust_force_vector
mdot_off_design = results_off_design.vehicle_mass_rate
Isp_off_design = results_off_design.specific_impulse
#Specify the expected values
expected = Data()
expected.thrust = 338740.93039999995
expected.mdot = 23.11959727
expected.Isp = 1494.05374047
#error data function
error = Data()
error.thrust_error = (F[0][0] - expected.thrust)/expected.thrust
error.mdot_error = (mdot[0][0] - expected.mdot)/expected.mdot
error.Isp_error = (Isp[0][0]- expected.Isp)/expected.Isp
print error
for k,v in error.items():
assert(np.abs(v)<1e-6)
return示例3: energy_network
# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import mdot [as 别名]
#.........这里部分代码省略.........
ram.tag = 'ram'
# add to the network
scramjet.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.90
inlet_nozzle.pressure_ratio = 1.0
inlet_nozzle.compressibility_effects = 3.0
inlet_nozzle.compression_levels = 3.0
inlet_nozzle.theta = [0.10472,0.122173,0.226893]
# add to network
scramjet.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.90
combustor.pressure_ratio = 1.0
combustor.area_ratio = 2.0
combustor.fuel_data = SUAVE.Attributes.Propellants.Liquid_H2()
combustor.burner_drag_coefficient = 0.01
combustor.fuel_equivalency_ratio = 1.0
# add to network
scramjet.append(combustor)
# ------------------------------------------------------------------
# Component 4 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Supersonic_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.9
nozzle.pressure_expansion_ratio = 1.1
# add to network
scramjet.append(nozzle)
# ------------------------------------------------------------------
# Component 5 - Thrust
# instantiate
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='thrust'
# setup
thrust.total_design = scramjet.number_of_engines*180000.0 * Units.N
# add to network
scramjet.thrust = thrust
#size the ramjet
scramjet_sizing(scramjet,size.mach_number,size.altitude)
print("Design thrust :",scramjet.design_thrust)
print("Sealevel static thrust :",scramjet.sealevel_static_thrust)
results_design = scramjet(state_sizing)
results_off_design = scramjet(state_off_design)
F = results_design.thrust_force_vector
mdot = results_design.vehicle_mass_rate
Isp = results_design.specific_impulse
F_off_design = results_off_design.thrust_force_vector
mdot_off_design = results_off_design.vehicle_mass_rate
Isp_off_design = results_off_design.specific_impulse
#Specify the expected values
expected = Data()
expected.thrust = 180000.0
expected.mdot = 7.8394948
expected.Isp = 2356.0590883
#error data function
error = Data()
error.thrust_error = (F[0][0] - expected.thrust)/expected.thrust
error.mdot_error = (mdot[0][0] - expected.mdot)/expected.mdot
error.Isp_error = (Isp[0][0]- expected.Isp)/expected.Isp
print(error)
for k,v in list(error.items()):
assert(np.abs(v)<1e-6)
return示例4: energy_network
# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import mdot [as 别名]
#.........这里部分代码省略.........
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
# Component 10 - Thrust
# to compute thrust
# instantiate
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='thrust'
# setup
thrust.total_design =42383.01818423
# add to network
turbofan.thrust = thrust
#bypass ratio closer to fan
numerics = Data()
eta=1.0
#size the turbofan
turbofan_sizing(turbofan,0.8,10000.0)
print "Design thrust ",turbofan.design_thrust
print "Sealevel static thrust ",turbofan.sealevel_static_thrust
results_design = turbofan(state_sizing)
results_off_design=turbofan(state_off_design)
F = results_design.thrust_force_vector
mdot = results_design.vehicle_mass_rate
F_off_design=results_off_design.thrust_force_vector
mdot_off_design = results_off_design.vehicle_mass_rate
#Test the model
#Specify the expected values
expected = Data()
expected.thrust = 42383.01818423
expected.mdot = 0.7657905
#error data function
error = Data()
error.thrust_error = (F[0][0] - expected.thrust)/expected.thrust
error.mdot_error = (mdot[0][0]-expected.mdot)/expected.mdot
print error
for k,v in error.items():
assert(np.abs(v)<1e-4)
return