Aerodynamics

tuduam.aerodynamics.component_drag()

tuduam.aerodynamics.drag_coefficient(aero, wing, alpha, m)

Return the drag coefficient for a specific angle of attack

Parameters:

• wing (SingleWing) – SingleWing dataclass

• alpha (float) – Angle of attack

• m (_type_) – number of points along the span (an odd number).

tuduam.aerodynamics.l_function(lam, spc, y, n, eps=1e-10)

Weissinger-L function, formulation by De Young and Harper.

Parameters:

• lam (float (radians)) – quarter chord sweep

• spc (float) – local span/chord

• y (float) – y/l = y*

• n (float) – eta/l = eta*

• eps (float , optional) – machine error taking into account , defaults to 1e-10

Returns:

Weisinger L function output

Return type:

float

tuduam.aerodynamics.lift_curve_slope(aero, wing, plot=False)

Returns

Parameters:

• flight_perf (FlightPerformance) – FlightPerfomance datat structurer

• vtol (VTOL) – VTOL data struct

• wing (SingleWing) – SingleWing data struct

• m (int) – number of points along the span (an odd number).

tuduam.aerodynamics.lift_distribution(aero, wing, alpha, rho, velocity)

returns a functions which outpouts the sectional lift for a given spanwise position

Parameters:

• aero (_type_) – _description_

• wing (_type_) – _description_

• alpha (_type_) – _description_

• rho (_type_) – _description_

• velocity (_type_) – _description_

Returns:

ccl: cl * local chord (proportional to sectional lift)

Return type:

_type_

tuduam.aerodynamics.planform_geometry(flight_perf, vtol, wing)

The following functions sizes the wing planform based on the specified wing loading and maximum take off weight. All attributes are assigned to the wing data struct. Note that x_lemac is given in the local coordinate system of te wing. That is the the coordinate system attached to the wing.

Parameters:

• flight_perf (FlightPerformance) – FlightPerformance data structure

• vtol (VTOL) – VTOL data structure

• wing (SingleWing) – SingleWing data structure

tuduam.aerodynamics.weissinger_l(aero, wing, alpha_root, plot=False)

Weissinger-L method for a swept, tapered, twisted wing.

Parameters:

• wing (SingleWing) – SingleWing datastructure, requires chord_root, chord_tip, quarterchord_sweep and washout

• alpha_root (float (radians)) – Angle of attack at the root

• m (integer (odd number)) – number of points along the span

• plot (bool, optional) – request to plot or not, defaults to False

Returns:

y: vector of points along span cl: local 2D lift coefficient cl ccl: cl * local chord (proportional to sectional lift) al_i: local induced angle of attack CL: lift coefficient for entire wing CDi: induced drag coefficient for entire wing

Return type:

tuple