UEQR:

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   Computes the exhaust velocity of a rocket from fuel lower heating
   value.
   The exhaust pressures are used as a ratio so can be any units.

   Type UEQR for a demo.

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   Form:
   uE = UEQR( qR, gamma, p0, pE )
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   ------
   Inputs
   ------
   qR            (1,1)   Heating value          (J/kg)
   gamma         (1,1)   Ratio of specific heats
   p0            (1,1)   Combustion pressure    (N/m^2)
   pE            (1,:)   Exhaust pressure       (N/m^2)

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

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Children:

Common: General/StdAtm
Common: Graphics/Plot2D
Propulsion: Chemical/QRHydrogen