IdealRkt:

Path: Propulsion/Rocket

% Computes the thrust and exhaust velocity for an ideal rocket. 
 p0 or e may be vectors. If p0 or e is an array then the other will be turned
 into an array of equal length.
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   Form:
   [thrust, uE, iSP, cT, pRatio] = IdealRkt( g, aStar, p0, pA, t0, e, m )
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   ------
   Inputs
   ------
   g            (1,1)  Ratio of specific heats
   aStar        (1,1)  Throat area (m^2)
   p0           (n)    Chamber pressure after heating (N/m^2)
   pA           (1,1)  Ambient pressure (N/m^2)
   t0           (1,1)  Temperature after heating (deg-K)
   e            (m)    Area ratio (exit area/throat area)
   m            (1,1)  Molecular weight (kg/mole)

   -------
   Outputs
   -------
   thrust       (n,m)  Thrust level (N)
   uE           (n)    Exhaust velocity (m/sec)
   iSP          (n)    Specific impulse (sec)
   cT           (m)    Thrust coefficient
   pRatio       (m)    Pressure ratio

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Children:

Common: Graphics/Mesh2
Common: Graphics/Plot2D
Propulsion: Rocket/TCoeff
Propulsion: Rocket/V2Isp
SC: Environs/MolWt2R

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