Issue with Internal Combustion Propeller

[Marilia Fagundes]

Hello everyone,

I am developing a code to optimize the range of a Cessna 182, but I am encountering some issues with the aircraft's propulsion modeling.

The setup is similar with the one from the C172 tutorial:

   # ------------------------------------------------------------------
    #   Piston Propeller Network
    # ------------------------------------------------------------------    
   
    # build network
    net                                         = SUAVE.Components.Energy.Networks.Internal_Combustion_Propeller()
    net.tag                                     = 'internal_combustion'
    net.number_of_engines                       = 1.
    net.identical_propellers                    = True
    net.nacelle_diameter                        = 42 * Units.inches
    net.engine_length                           = 0.01 * Units.inches
    net.areas                                   = Data()
    net.rated_speed                             = 2000. * Units.rpm
    net.rated_power                             = 230.  * Units.hp
    net.areas.wetted                            = 0.01

    # Component 1 the engine                    
    engine                                  = SUAVE.Components.Energy.Converters.Internal_Combustion_Engine()
    engine.sea_level_power                  = 180. * Units.horsepower   #!!!!!!
    engine.flat_rate_altitude               = 0.0
    engine.speed                            = 2000. * Units.rpm         #!!!!
    engine.power_specific_fuel_consumption  = 0.620166 #lb/h-hp (inside Internal Combustion Engine, it will be converted)
   
   
    # add the network to the vehicle
    net.engines.append(engine)

    # net = propeller_design(net)
   
    # Component 2 the PROPELLER
    # Design the Propeller
    prop = SUAVE.Components.Energy.Converters.Propeller()


    prop.number_blades       = 3.0
    prop.freestream_velocity = 135.*Units['mph']    
    prop.angular_velocity    = 1300.  * Units.rpm # 2400      !!!!!!!
    prop.tip_radius          = 82./2. * Units.inches
    prop.hub_radius          = 8.     * Units.inches
    prop.design_Cl           = 0.8
    prop.design_altitude     = 12000. * Units.feet
    prop.origin              = [[2.,2.5,0.784]]  #  prop influence              
    prop.symmetry            = True
    prop.design_power            = .64 * 180. * Units.horsepower
    prop.variable_pitch          = False
    prop                     = propeller_design(prop)    
    net.propellers.append(prop)  

    # add the network to the vehicle
    vehicle.append_component(net)       

But I am recieving this error:

File "C:\Users\maril\AppData\Local\Programs\Python\Python310\lib\site-packages\suave-2.5.2-py3.10.egg\SUAVE\Components\Energy\Networks\Internal_Combustion_Propeller.py", line 120, in evaluate_thrust
    prop.inputs.omega = conditions.propulsion.rpm
AttributeError: 'Conditions' object has no attribute 'rpm'

Could someone help me understand the issue? 

Here are the code files: https://github.com/mariliafagundes/SUAVE_C182

Thanks.