Glide:

Path: ACPro/ACPerformance

% Compute glide angle, range and velocity..

   Type Glide for a demo of a Cessna 172. In this example we add a 
   parasitic drag cofficient of 0.21 to account for the fuselage.

   Since version 5.
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   Form:
   [angle, v, r] = Glide( h, v, d, cL  )
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   ------
   Inputs
   ------
   h               (1,:) Altitude (m)
   v               (1,:) Velocity (m/s)
   d                (.)  Data structure
                         .mass         (1,1) Mass (kg)
                         .s            (1,1) Reference area (m^2)
                         .length       (1,1) Representative length (e.g. mean chord) (m)
                         .oswaldEff    (1,1) Oswald efficiency factor (optional)
                         .aspectRatio	(1,1) Aspect ratio for wing (length/mean chord)
                         .thickness    (1,1) Ratio of length to thickness
                         .m1Peak       (1,1) Peak at M = 1 an alternative to zetaTrans
   cL              (1,:) Lift coefficient (otpional)

   -------
   Outputs
   -------
   angle          (1,:) Glide angle
   v              (1,:) Glide velocity
   r              (1,:) Glide range

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   Reference: Anderson, J. D., "Introduction to Flight 3rd Edition,",
              McGraw-Hill 1989, pp 294-297.
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Children:

ACPro: ACProAerodynamics/DragCoeff
Common: Atmosphere/StdAtm
Common: Database/Constant
Common: Graphics/Plot2D

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