aerotools package

Submodules

aerotools.vpm module

class aerotools.vpm.Airfoil(NACA_Name, Chord_Length=1, NUM_SAMPLES=100, Angle_Of_Attack=0)[source]

Bases: object

Airfoil handles calculations made on 4-digit series NACA airfoil.

The Airfoil class calculates the x-y coordinates of all boundary points on an NACA 4-digit series airfoil.

Parameters:
  • NACA_ID – The NACA 4-digit series airfoil name i.e. “NACA0012”
  • chord – The chord length of the airfoil
  • NUM_SAMPLES – The number of samples / panels considered
  • angle_of_attack – The angle of attack of the airfoil
  • max_camber – The maximum camber of the airfoil i.e “0/100, 1/100”
  • position_max_camber – The position of the max. camber i.e. “4/100”
  • thickness – The maximum thickness of the airfoil i.e. “12/100”, “08/100”
  • x_boundary_points – The x-locations of each boundary point on the airfoil
  • y_boundary_points – The y-locations of each boundary point on the airfoil
  • full_coefficient_lift – The coefficient of lift of the airfoil
  • pressure_coefficient – The pressure coefficient at each (x,y) point
get_airfoil_coordinates()[source]

Returns the coordinates of the airfoil.

Returns:An array of x-coordinates and y-coordinates of boundary points. [X,Y]
Return type:tuple
get_coefficient_lift()[source]

Returns the coefficient of lift.

Returns:The airfoil’s coefficient of lift (per meter span), Cl.
Return type:float
get_panel_coordinates()[source]

Returns the coordinates of the midpoints of the panels.

Returns:An array of x-coordinates and y-coordiantes of the panel mid- points. [X, Y]
Return type:tuple
get_pressure_coefficients()[source]

Returns the pressure coefficient at the midpoint of each panel.

Returns:Pressure coefficient at each boundary point, Cp.
Return type:float[]
set_airfoil(NACA_ID)[source]

Sets the airfoil type used.

Parameters:NACA_ID – The 4-digit series airfoil name. Example: ‘NACA0012’
set_angle_of_attack(angle)[source]

Sets the angle of attack to use for next calculations.

Parameters:angle – The new angle of attack
set_chord_length(length)[source]

Sets the chord length used in the calculations.

Parameters:length – The chord length of the airfoil.
set_num_samples(samples)[source]

Sets the number of panels used for sampling the airfoil.

Parameters:samples – The number of samples / panels used for airfoil calculations.

Module contents