UEO2H2:

Path: Propulsion/Rocket

% Computes the exhaust velocity of a O2/H2 rocket.

   Since version 2.
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   Form:
   uE = UEO2H2( n, t0, p0, pE )
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   ------
   Inputs
   ------
   n             (1,:)   Number of molecules of H2 per O2 molecule
   t0            (1,1)   Combustion temperature (deg-K)
   p0            (1,1)   Combustion pressure    (N/m^2)
   pE            (1,1)   Exhaust pressure       (N/m^2)

   -------
   Outputs
   -------
   uE            (1,:)   Exhaust velocity

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Children:

Propulsion: Gas/Gamma
Propulsion: Gas/MolWt
Propulsion: Rocket/UE

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