UE:

Path: Propulsion/Rocket

% Computes the ideal exhaust velocity of a rocket.

   Since version 2.
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   Form:
   uE = UE( gamma, m, t0, p0, pE )
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   ------
   Inputs
   ------
   gamma         (1,n)   Ratio of specific heats
   m             (1,m)   Molecular weight of the combustion products kg/mole
   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            (m,n)   Exhaust velocity

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Children:

Common: Graphics/Mesh2
SC: Environs/MolWt2R

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