RCAIDE.Library.Methods.Performance.aircraft_aerodynamic_analysis
aircraft_aerodynamic_analysis#
- aircraft_aerodynamic_analysis(aerodynamics_analysis=None, angle_of_attack_range=None, Mach_number_range=None, control_surface_deflection_range=array([[0]]), altitude=0, delta_ISA=0)[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_attack_range (ndarray) – Array of angle of attack values to evaluate [radians]
Mach_number_range (ndarray) – Array of Mach numbers to evaluate
control_surface_deflection_range (ndarray, optional) – Array of control surface deflection angles [radians], default [[0]]
altitude (float, optional) – Altitude for atmospheric properties [m], default 0
delta_ISA (float, optional) – Temperature offset from ISA conditions [K], default 0
use_surrogate (bool, optional) – Flag for using surrogate model in analysis, default True
model_fuselage (bool, optional) – Flag for including fuselage effects, default True. Of note, fuselage modeling can sometimes be difficult for VLM solvers.
- 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
- 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