RCAIDE.Library.Mission.Common.Update.aerodynamics

aerodynamics

aerodynamics(segment)

Gets aerodynamics conditions

Assumptions: +X out nose +Y out starboard wing +Z down

Inputs:

segment.analyses.aerodynamics_model [Function] aerodynamics_model.settings.maximum_lift_coefficient [unitless] aerodynamics_model.vehicle.reference_area [meter^2] segment.state.conditions.freestream.dynamic_pressure [pascals]

Outputs:

conditions.aerodynamics.coefficients.lift.total [unitless] conditions.aerodynamics.coefficients.drag.total [unitless] conditions.frames.wind.force_vector [newtons] conditions.frames.wind.drag_force_vector [newtons]

Properties Used: N/A