AircraftEquilibrium:

Path: ACPro/ACPerformance

% Computes the equilibrium thrust and wing area.
   This function determines the required thrust and wing area to
   balance the drag and gravity forces at any flight condition. You can
   enter flight path angle, altitude, mach number and the drag data
   structure. gamma, h, and m can be vectors. The drag data structure
   can be an array to enter different wing characteristics for segments
   of the wing, for example in a double delta wing.

   Type AircraftEquilibrium for a demo.
   Since version 5.
--------------------------------------------------------------------------
   Form:
   [thrust, s] = AircraftEquilibrium( mass, gamma, h, m, d )
--------------------------------------------------------------------------

   ------
   Inputs
   ------ 
   mass            (1,1)  Mass (kg)
   gamma           (1,:)  Flight path angle (rad)
   h               (1,:)  Altitude (m)
   m               (1,:)  Mach number
   d               (:)    Drag data structure  (See LiftAndDrag)

   -------
   Outputs
   -------
   thrust          (1,:) Thrust
   s               (1,:) Wing area

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   See also LDDeltaWing
--------------------------------------------------------------------------

Children:

ACPro: ACDesign/AircraftDragDataStructures
ACPro: ACProAerodynamics/LDDeltaWing
Common: Atmosphere/StdAtm
Common: Graphics/Plot2D

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