RCAIDE.Library.Methods.Performance.aircraft_aerodynamic_analysis
aircraft_aerodynamic_analysis#
- aircraft_aerodynamic_analysis(analyses=None, angle_of_attacks=None, mach_numbers=None, non_dimensional_reynolds_numbers=None, temperatures=None, overwrite_reference=True, altitude=None)[source]#
Computes aerodynamic coefficients across ranges of angle of attack and Mach numbers using vortex lattice methods.
- Parameters:
vehicle (Vehicle) – The vehicle instance to be analyzed
angle_of_attacks (ndarray) – Array of angle of attack values to evaluate [radians]
mach_numbers (ndarray) – Array of Mach numbers to evaluate
altitude (float, optional) – Altitude for atmospheric properties [m], default 0
- Returns:
results –
- Container of analysis results including:
- Machndarray
Evaluated Mach numbers
- alphandarray
Evaluated angles of attack [rad]
- lift_coefficientndarray
Computed lift coefficients
- drag_coefficientndarray
Computed drag coefficients
- moment_coefficientndarray
Computed Y-moment coefficients
- Return type:
Notes
The function uses the US Standard Atmosphere 1976 model for atmospheric properties and evaluates aerodynamic coefficients using vortex lattice methods. Can use a surrogate model for faster evaluation or just direct evaluation of the aerodynamics.
- Major Assumptions
Flow is steady and inviscid
Small angle approximations apply
Linear aerodynamics
Atmospheric properties follow US Standard Atmosphere 1976