RocketFromUEAndT:

Path: Propulsion/Rocket

% Computes the thrust and exhaust velocity as a function of pressure.
   Utilizes the engine data measured at vacuum and a specified reference
   pressure.

   Type RocketFromUEAndT for a demo of the Shuttle Main Engine (SME).

   Since version 2014.1
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   Form:
   [t, uE] = RocketFromUEAndT( uE0, uEA, t0, tA, pA, p )
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   ------
   Inputs
   ------
   uE0	(1,1) Exhaust velocity in vacuum
   uEA (1,1) Exhaust velocity at pressure pA
   t0  (1,1) Thrust in vacuum
   tA  (1,1) Thrust at pressure pA
   pA  (1,1) Reference pressure
   p   (1,:) Pressure

   -------
   Outputs
   -------
   t   (1,1) Thrust
   uE  (1,1) Exhaust velocity

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Children:

Common: Graphics/Plot2D

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