RocketH2O2:

Path: Propulsion/Chemical

% H2/O2 rocket model.

   Type RocketH2O2 for a demo of the Space Shuttle Main Engine at sea 
   level.

   If p0 is any character it will return a default data structure.

   Since version 2014.1
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   Form:
   [thrust, uE, qR] = RocketH2O2( p0, pA, aStar, aE, f, tP )
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   ------
   Inputs
   ------
   p0      (1,1) Chamber pressure      (N/m^2)
   pA      (1,1) Ambient pressure      (N/m^2)
   aStar   (1,1) Throat area           (m^2)
   aE      (1,1) Exit area             (m^2)
   f       (1,1) Mixture ratio         (kg O2/kg H2)
   tP      (1,1) Preheat temperature	(deg-K)

   ------
   Outputs
   -------
   thrust  (1,1) Thrust                (N)
   uE      (1,1) Exhaust velocity      (m/s)
   qR      (1,1) Energy per unit mass  (J/kg)

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   References: http://en.wikipedia.org/wiki/Space_Shuttle_Main_Engine
               Hill, P. and C. Peterson, "Mechanics and Thermodynamics
               of Propulsion", p. 353-361.
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