RocketH2:

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   Computes the thrust and exhaust velocity of an H2 rocket.
   Thrust is per unit area. 

   Type RocketH2 for a demo.

   qR must be the energy per unit mass of fuel + oxygen.

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   Form:
   [thrust, uEQ] = RocketH2( p0, pA, aStar, aE, qR, gamma, f )
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   ------
   Inputs
   ------
   p0            (1,1)   Combustion pressure    (N/m^2)
   pA            (1,:)   Exhaust pressure       (N/m^2)
   aStar         (1,1)   Throat area            (m^2)
   aE            (1,1)   Exit area              (m^2)
   qR            (1,1)   Energy fuel            (J/kg)
   gamma         (1,1)   Ratio of specific heats
   f             (1,1)   H2/O2 ratio (2 = stoichemetric)

   -------
   Outputs
   -------
   thrust        (1,:)   Thrust                 (N)
   uEQ           (1,:)   Exhaust velocity       (m/s)

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Children:

Common: General/StdAtm
Common: Graphics/Plot2D
Propulsion: Chemical/IsentropicExpansion
Propulsion: Chemical/MachFromAreaRatio
Propulsion: Chemical/QRHydrogen
Propulsion: Chemical/UEQR