NuclearThermalUE:

Path: Propulsion/Nuclear

% Compute the exhaust velocity for a nuclear rocket with H2 fuel.
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   Form:
   uE = NuclearThermalUE( t, fuel )
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   ------
   Inputs
   ------
   t           (1,:) Temperature (deg-K)
   fuel        (1,:) Fuel name

   -------
   Outputs
   -------
   uE          (1,:) Exhaust velocity (m/sec)

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Children:

Common: Graphics/Plot2D
Propulsion: Chemical/Fuels
Propulsion: Rocket/UE

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