Python Data.mach_number方法代码示例

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import mach_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

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import mach_number [as 别名]
def call_SU2(conditions,settings,geometry):
    """Calculates lift and drag using SU2

    Assumptions:
    None

    Source:
    N/A

    Inputs:
    conditions.
      mach_number        [-]
      angle_of_attack    [radians]
    settings.
      half_mesh_flag     <boolean> Determines if a symmetry plane is used
      parallel           <boolean>
      processors         [-]
      maximum_iterations [-]
    geometry.
      tag
      reference_area     [m^2]

    Outputs:
    CL                   [-]
    CD                   [-]

    Properties Used:
    N/A
    """      

    half_mesh_flag = settings.half_mesh_flag
    tag            = geometry.tag
    parallel       = settings.parallel
    processors     = settings.processors 
    iters          = settings.maximum_iterations
    
    SU2_settings = Data()
    if half_mesh_flag == False:
        SU2_settings.reference_area  = geometry.reference_area
    else:
        SU2_settings.reference_area  = geometry.reference_area/2.
    SU2_settings.mach_number     = conditions.aerodynamics.mach
    SU2_settings.angle_of_attack = conditions.aerodynamics.angle_of_attack / Units.deg
    SU2_settings.maximum_iterations = iters
    
    # Build SU2 configuration file
    write_SU2_cfg(tag, SU2_settings)
    
    # Run SU2
    CL, CD = call_SU2_CFD(tag,parallel,processors)
        
    return CL, CD

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import mach_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

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import mach_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

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import mach_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