RCAIDE.Library.Methods.Geometry.Airfoil.compute_airfoil_properties
compute_airfoil_properties#
- compute_airfoil_properties(airfoil_geometry, airfoil_polar_files=None, use_pre_stall_data=True)[source]#
This computes the aerodynamic properties and coefficients of an airfoil in stall regimes using pre-stall characterstics and AERODAS formation for post stall characteristics. This is useful for obtaining a more accurate prediction of wing and blade loading as well as aeroacoustics. Pre stall characteristics are obtained in the form of a text file of airfoil polar data obtained from airfoiltools.com
- Assumptions:
None
- Source
None
Inputs: airfoil_geometry <data_structure> airfoil_polar_files <string> boundary_layer_files <string> use_pre_stall_data [Boolean] Outputs: airfoil_data.
cl_polars [unitless] cd_polars [unitless] aoa_sweep [unitless]
Properties Used: N/A
- compute_extended_polars(airfoil_cl, airfoil_cd, airfoil_aoa, AoA_sweep_deg, geometry, use_pre_stall_data)[source]#
Computes the aerodynamic polars of an airfoil over an extended angle of attack range
Assumptions: Uses AERODAS formulation for post stall characteristics Source: Models of Lift and Drag Coefficients of Stalled and Unstalled Airfoils in Wind Turbines and Wind Tunnels by D Spera, 2008
Inputs: airfoil_cl [unitless] airfoil_cd [unitless] airfoil_aoa [degrees] AoA_sweep_deg [unitless] geometry [N/A] use_pre_stall_data [boolean] Outputs: CL [unitless] CD [unitless]
Properties Used: N/A
- apply_pre_stall_data(AoA_sweep_deg, airfoil_aoa, airfoil_cl, airfoil_cd, CL, CD)[source]#
Applies prestall data to lift and drag curve slopes
Assumptions: None
Source: None
Inputs: AoA_sweep_deg [degrees] airfoil_aoa [degrees] airfoil_cl [unitless] airfoil_cd [unitless] CL [unitless] CD [unitless]
Outputs CL [unitless] CD [unitless]
Properties Used: N/A
- compute_boundary_layer_properties(airfoil_geometry, Airfoil_Data)[source]#
Computes the boundary layer properties of an airfoil for a sweep of Reynolds numbers and angle of attacks.
Source: None
Assumptions: None
Inputs: airfoil_geometry <data_structure> Airfoil_Data <data_structure>
Outputs: Airfoil_Data <data_structure>
Properties Used: N/A