本文整理汇总了Python中SUAVE.Core.Data.reynolds_number方法的典型用法代码示例。如果您正苦于以下问题：Python Data.reynolds_number方法的具体用法？Python Data.reynolds_number怎么用？Python Data.reynolds_number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.reynolds_number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: main
# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import reynolds_number [as 别名]
def main():
configs, analyses = full_setup()
simple_sizing(configs)
configs.finalize()
analyses.finalize()
# weight analysis
weights = analyses.configs.base.weights
breakdown = weights.evaluate()
# mission analysis
mission = analyses.missions.base
results = mission.evaluate()
# print weight breakdown
print_weight_breakdown(configs.base,filename = 'weight_breakdown.dat')
# print engine data into file
print_engine_data(configs.base,filename = 'B737_engine_data.dat')
# print parasite drag data into file
# define reference condition for parasite drag
ref_condition = Data()
ref_condition.mach_number = 0.3
ref_condition.reynolds_number = 12e6
print_parasite_drag(ref_condition,configs.cruise,analyses,'B737_parasite_drag.dat')
# print compressibility drag data into file
print_compress_drag(configs.cruise,analyses,filename = 'B737_compress_drag.dat')
# print mission breakdown
print_mission_breakdown(results,filename='B737_mission_breakdown.dat')
# load older results
#save_results(results)
old_results = load_results()
# plt the old results
plot_mission(results)
plot_mission(old_results,'k-')
# check the results
check_results(results,old_results)
## # print some results, for check agaist Aviation paper
## end_segment = results.segments[-1]
## time = end_segment.conditions.frames.inertial.time[-1,0] / Units.min
## distance = end_segment.conditions.frames.inertial.position_vector[-1,0] / Units.nautical_miles
## mass_end = end_segment.conditions.weights.total_mass[-1,0]
## mass_begin = results.segments[0].conditions.weights.total_mass[0,0]
## fuelburn = (mass_begin- mass_end) / Units.lbs
##
## print 'Time: {:5.0f} min , Distance: {:5.0f} nm ; FuelBurn: {:5.0f} lbs'.format(time,distance,fuelburn)
return示例2: main
# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import reynolds_number [as 别名]
def main():
configs, analyses = full_setup()
simple_sizing(configs, analyses)
configs.finalize()
analyses.finalize()
# mission analysis
mission = analyses.missions.base
results = mission.evaluate()
# print weight breakdown
#print_weight_breakdown(configs.base,filename = 'weight_breakdown.dat')
# print engine data into file
#print_engine_data(configs.base,filename = 'B737_engine_data.dat')
# print parasite drag data into file
# define reference condition for parasite drag
ref_condition = Data()
ref_condition.mach_number = 0.3
ref_condition.reynolds_number = 12e6
#print_parasite_drag(ref_condition,configs.cruise,analyses,'B737_parasite_drag.dat')
# print compressibility drag data into file
#print_compress_drag(configs.cruise,analyses,filename = 'B737_compress_drag.dat')
# print mission breakdown
#print_mission_breakdown(results,filename='B737_mission_breakdown.dat')
# load older results
#save_results(results)
old_results = load_results()
# plt the old results
#save_results(results)
plot_mission(results)
plot_mission(old_results,'k-')
plt.show(block=True)
# check the results
check_results(results,old_results)
return示例3: main
# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import reynolds_number [as 别名]
def main():
# define the problem
configs, analyses = full_setup()
configs.finalize()
analyses.finalize()
# weight analysis
weights = analyses.configs.base.weights
breakdown = weights.evaluate()
# mission analysis
mission = analyses.missions
results = mission.evaluate()
# print engine data into file
print_engine_data(configs.base,filename = 'engine_data.dat')
# print parasite drag data into file
# define reference condition for parasite drag
ref_condition = Data()
ref_condition.mach_number = 0.3
ref_condition.reynolds_number = 20e6
print_parasite_drag(ref_condition,configs.cruise,analyses,'parasite_drag.dat')
# print compressibility drag data into file
print_compress_drag(configs.cruise,analyses,filename = 'compress_drag.dat')
# print mission breakdown
print_mission_breakdown(results,filename='mission_breakdown.dat')
# load older results
#save_results(results)
old_results = load_results()
# plt the old results
plot_mission(results)
plot_mission(old_results,'k-')
plt.show()
# check the results
check_results(results,old_results)
return示例4: post_process
# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import reynolds_number [as 别名]
#.........这里部分代码省略.........
payload,
820., #Fuel density
vehicle.wings.horizontal_stabilizer.sweep,
vehicle.wings.horizontal_stabilizer.spans.projected,
vehicle.wings.horizontal_stabilizer.chords.root,
vehicle.wings.vertical_stabilizer.sweep,
vehicle.wings.vertical_stabilizer.taper,
vehicle.wings.vertical_stabilizer.chords.root
# QUESTIONABLE: CL_alpha, CM_alpha, Lift distribution, CM_delta, CL_delta
])
output_indices = ["A",
"S",
"sweep",
"taper",
"c_r",
"b",
"d_fus",
"l_fus",
"c_mac",
"y_fuselages",
"CL_max_TO",
"CL_max_landing",
"CL_max_clean",
"v_landing",
"v_cr",
"N_engines",
"m_engine_wet",
"m_engine_dry",
"d_engine",
"m_fuel",
"MTOW",
"OEW",
"m_landing",
"m_wing",
"m_fus",
"m_landing_gear",
"m_payload",
"rho_fuel",
"sweep_h",
"b_h",
"c_r_h",
"sweep_v",
"taper_v",
"c_r_v"
]
# print output_array[output_indexes.index("c_r_v")]
# print output_array[-1]
# print vehicle.weight_breakdown
np.save(output_folder+"output_array.npy",output_array)
np.save(output_folder+"output_indices.npy",output_indices)
np.save(output_folder+"output_array_segments.npy",output_array_segments)
np.save(output_folder+"output_segment_indices.npy",output_segment_indices)
for value in unscaled_inputs:
problem_inputs.append(value)
file_out = open(output_folder+'results.txt', 'ab')
file_out.write('fuel weight = ')
file_out.write(str(summary.base_mission_fuelburn))
file_out.write(', inputs = ')
file_out.write(str(problem_inputs))
file_out.write('\n')
file_out.close()
print_weight_breakdown(nexus.vehicle_configurations.base, filename=output_folder + 'weight_breakdown.dat')
#
# # print engine data into file
print_engine_data(nexus.vehicle_configurations.base, filename=output_folder + 'engine_data.dat')
#
# # print parasite drag data into file
# # define reference condition for parasite drag
ref_condition = Data()
ref_condition.mach_number = 0.7 # FIXME
ref_condition.reynolds_number = 7e6 # FIXME
Analyses = Data()
Analyses.configs = nexus.analyses
print_parasite_drag(ref_condition, nexus.vehicle_configurations.cruise, Analyses,
filename=output_folder + 'parasite_drag.dat')
#
# print compressibility drag data into file
# print Analyses
print_compress_drag(nexus.vehicle_configurations.cruise, Analyses, filename=output_folder + 'compress_drag.dat')
# print mission breakdown
print_mission_breakdown(nexus.results.base,
filename=output_folder + 'mission_breakdown.dat') # FIXME fuel weight adds aerosol = wrong!!!!!
return nexus