RocketVariableUEAndT:

Path: Propulsion/Rocket

% Computes the thrust and exhaust velocity given one pair [uE0,t0].
   This assumes that the available energy from combustion and the engine
   efficiency does not change. The relationship is parabolic.
   You can also input T instead of uE and the output will be uE. 
   This relationship does not extend beyond stochiometric conditions.

   Type RocketVariableUEAndT for a demo for the RL10B-2.

   Since version 2014.1
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   Form:
   t = RocketVariableUEAndT( uE0, t0, uE )
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   ------
   Inputs
   ------
   uE0	(1,1) Reference exhaust velocity (m/s)
   t0  (1,1) Reference thrust in vacuum (N)
   uE  (1,:) Exhaust velocity (m/s)

   -------
   Outputs
   -------
   t   (1,:) Thrust (N)

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Children:

Common: Graphics/Plot2D

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