aerodynamics¶
class description¶
-
class
aerodynamics.
Aerodynamics
(**kwargs)[source]¶ Bases:
openmdao.core.explicitcomponent.ExplicitComponent
Computes aerodynamic forces and Mach number along the trajectory.
The Aerodynamics component requires the following inputs:
inputs['c_l']
: aircraft lift coefficient [-]inputs['c_d']
: aircraft drag coefficient [-]inputs['rho_0']
: ambient density [kg/m3]inputs['c_0']
: ambient speed of sound [m/s]inputs['v']
: aircraft velocity [m/s]
The Aerodynamics component computes the following outputs:
outputs['q']
: ambient dynamic pressure [Pa]outputs['L']
: aircraft lift [N]outputs['D']
: aircraft drag [N]outputs['M_0']
: ambient Mach number [-]
-
compute
(inputs: openmdao.vectors.default_vector.DefaultVector, outputs: openmdao.vectors.default_vector.DefaultVector)[source]¶ Compute outputs given inputs. The model is assumed to be in an unscaled state.
- Parameters
inputs (Vector) – Unscaled, dimensional input variables read via inputs[key].
outputs (Vector) – Unscaled, dimensional output variables read via outputs[key].
discrete_inputs (dict or None) – If not None, dict containing discrete input values.
discrete_outputs (dict or None) – If not None, dict containing discrete output values.
-
compute_partials
(inputs: openmdao.vectors.default_vector.DefaultVector, partials: openmdao.vectors.default_vector.DefaultVector)[source]¶ Compute sub-jacobian parts. The model is assumed to be in an unscaled state.
- Parameters
inputs (Vector) – Unscaled, dimensional input variables read via inputs[key].
partials (Jacobian) – Sub-jac components written to partials[output_name, input_name]..
discrete_inputs (dict or None) – If not None, dict containing discrete input values.
theory¶
The aircraft aerodynamic lift coefficient, \(C_L\), and drag coefficient, \(C_D\), are provided to the module in terms of a look-up table as a function of the wing angle of attack, \(\alpha\), and the flap and slat deflection angle, \(\theta_{flap}\) and \(\theta_{slat}\). The aircraft lift and drag forces are computed using the wing surface area, \(S\), and the dynamic pressure, \(q=\frac{1}{2}\rho v^2\), as follows: