Basic Descent

A Basic Descent performance model is comprised of a simple set of parameters that define the flight characteristics of the aircraft while descending.

Parameter	Description
Ceiling Altitude	Defines the maximum altitude above Mean Sea Level that may be specified as a procedure altitude for the aircraft. The ceiling describes the maximum altitude at which an aircraft can sustain level, non-accelerated flight. In general, an aircraft will not exceed the ceiling, but the ceiling could be violated by the Aviator in some instances, where required to complete a maneuver.
Airspeed	Define the aircraft's speed; select a reference from the drop-down menu - true airspeed (TAS), calibrated airspeed (CAS), equivalent airspeed (EAS), or Mach number.
Altitude Rate	Defines the constant rate at which the aircraft will climb and descend once established in a steady climb or descent.
Use Aero/Propulsion Fuel Flow	Select to use the fuel flow calculated by the aerodynamics and propulsion strategies defined in the active acceleration performance model; if the acceleration performance model is not set to calculate fuel flow, then fuel flow will not be calculated for this performance model, either.
Scale Fuel Flow by Non Std Density	Select to scale the fuel flow based on the aircraft's actual altitude. If this option is disabled, the fuel flow will be calculated at the Default Cruise Altitude (if available), or at sea level.
Sea Level Fuel Flow	Defines the amount of fuel used per unit of time selected, at sea level.
Initial Level Off for Acceleration	If enabled, the aircraft will level off and accelerate or decelerate until its airspeed is within the defined Relative airspeed tolerance, and only then begin its climb or descent. This models the common pilot practice of achieving the aircraft's optimal climb or descent airspeed at level flight before beginning a climb or descent.