fastoad.models.aerodynamics.components.cd_compressibility module

Compressibility drag computation.

class fastoad.models.aerodynamics.components.cd_compressibility.CdCompressibility(**kwargs)[source]

Bases: openmdao.core.explicitcomponent.ExplicitComponent

Computation of drag increment due to compressibility effects.

Formula from §4.2.4 of [DCAC14]. This formula can be used for aircraft before year 2000. Earlier aircraft have more optimized wing profiles that are expected to limit the compressibility drag below 2 drag counts. Until a better model can be provided, the variable tuning:aerodynamics:aircraft:cruise:CD:compressibility:characteristic_mach_increment allows to move the characteristic Mach number, thus moving the CD divergence to higher Mach numbers.

Store some bound methods so we can detect runtime overrides.

Parameters

**kwargs (dict of keyword arguments) – Keyword arguments that will be mapped into the Component options.

setup()[source]

Declare inputs and outputs.

Available attributes:

name pathname comm options

setup_partials()[source]

Declare partials.

This is meant to be overridden by component classes. All partials should be declared here since this is called after all size/shape information is known for all variables.

compute(inputs, outputs)[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.