RCAIDE.Library.Plots.Aerodynamics.plot_aerodynamic_coefficients

plot_aerodynamic_coefficients#

plot_aerodynamic_coefficients(results, save_figure=False, show_legend=True, save_filename='Aerodynamic_Coefficients', file_type='.png', width=11, height=7)[source]#

Creates a multi-panel visualization of aerodynamic coefficients throughout flight.

Parameters:

results (Results) –
RCAIDE results data structure containing:
- segments[i].conditions.aerodynamics.coefficients
  
  Coefficient data containing:
  
  lift.total[:,0,None]
  Total lift coefficient
  
  drag.total[:,0,None]
  Total drag coefficient
- segments[i].conditions.aerodynamics.angles
  
  Angle data containing:
  
  alpha[:,0]
  Angle of attack in radians
- segments[i].conditions.frames.inertial.time[:,0]
  Time history for each segment
- segments[i].tag
  Segment identifier string
save_figure (bool, optional) – Flag for saving the figure (default: False)
show_legend (bool, optional) – Flag to display segment legend (default: True)
save_filename (str, optional) – Name of file for saved figure (default: “Aerodynamic_Coefficients”)
file_type (str, optional) – File extension for saved figure (default: “.png”)
width (float, optional) – Figure width in inches (default: 11)
height (float, optional) – Figure height in inches (default: 7)

Returns:

fig

Return type:

matplotlib.figure.Figure

Notes

Creates visualization showing:

Aerodynamic performance metrics
Flight attitude history
Efficiency characteristics
Time evolution of coefficients

Major Assumptions

Quasi-steady aerodynamics
Small angle approximations
Incompressible flow
Linear lift curve slope
Negligible sideslip

Definitions

‘Lift Coefficient’: Non-dimensional lift force
‘Drag Coefficient’: Non-dimensional drag force
‘Angle of Attack’: Angle between airflow and reference line
‘L/D Ratio’: Measure of aerodynamic efficiency

plot_aerodynamic_coefficients#

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