RCAIDE.Library.Methods.Powertrain.Converters.Ducted_Fan.Performance.Blade_Element_Momentum_Theory.write_geometry

write_geometry#

write_geometry(dfdc_object, run_script_path)[source]#

Writes the ducted fan geometry to a case file for DFDC analysis.

Parameters:

  • dfdc_object (DFDCAnalysis) –

    Analysis object containing the following attributes:
    • geometryDuctedFan
      Ducted fan geometry with the following attributes:
      • tagstr

        Identifier for the ducted fan

      • lengthfloat

        Length of the ducted fan [m]

      • hub_radiusfloat

        Radius of the hub [m]

      • tip_radiusfloat

        Radius of the blade tip [m]

      • blade_clearancefloat

        Clearance between blade tip and duct [m]

      • number_of_rotor_bladesint

        Number of blades on the rotor

      • number_of_radial_stationsint

        Number of radial stations for blade definition

      • rotorData
        Rotor properties
        • percent_x_locationfloat

          Axial location of rotor as fraction of length

      • statorData
        Stator properties
        • percent_x_locationfloat

          Axial location of stator as fraction of length

      • cruiseData
        Cruise conditions
        • design_angular_velocityfloat

          Design angular velocity [rad/s]

        • design_freestream_velocityfloat

          Design freestream velocity [m/s]

        • design_reference_velocityfloat

          Design reference velocity [m/s]

      • hub_airfoilAirfoil

        Airfoil definition for hub

      • duct_airfoilAirfoil

        Airfoil definition for duct

  • run_script_path (str) – Path to the directory where the case file will be written

Return type:

None

Notes

This function generates a DFDC case file with the following sections:

  1. Header information including operating conditions

  2. Hub geometry definition

  3. Separator between geometry components

  4. Duct geometry definition

The function handles both NACA 4-series airfoils and custom airfoil definitions for the hub and duct. If no airfoil is specified, default NACA airfoils are used (0015 for hub, 2208 for duct).

The blade geometry is defined with linearly varying chord and twist distributions from hub to tip.

See also

RCAIDE.Library.Methods.Powertrain.Converters.Ducted_Fan.purge_files, RCAIDE.Library.Methods.Geometry.Airfoil.import_airfoil_geometry, RCAIDE.Library.Methods.Geometry.Airfoil.compute_naca_4series

make_header_text(dfdc_object, geometry)[source]#

This function writes the header using the template required for the DFDC executable to read

make_hub_text(dfdc_object, geometry)[source]#

This function writes the rotor using the template required for the DFDC executable to read

make_separator_text(dfdc_object, geometry)[source]#

This function writes the operating conditions using the template required for the DFDC executable to read

make_duct_text(dfdc_object, geometry)[source]#

This function writes the operating conditions using the template required for the DFDC executable to read