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   Computes the ideal thrust coefficient for a nozzle with a diverging portion.

   If no outputs are specified it will generate a plot. If both e and p
   are vectors it will create a mesh plot. If only one is a vector it will
   create an xy plot.
 
   If only g is specified it will use e = linspace(15,600) and p =
   logspace(2,4). If no inputs are specified g will be set equal to 1.2. To
   get the real thrust coefficient multiply the result by an efficiency
   factor (typically 0.98).

   inf is a legitimate pressure ratio but you cannot generate plots with it.

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   Form:
   [cF, x] = TCoeff( g, e, p )
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   Inputs
   ------
   g        (1,1) Ratio of specific heats for the gas
   e        (1,n) Area ratio (exit area/throat)
   p        (1,m) Chamber pressure/ambient pressure

   -------
   Outputs
   -------
   cF		 (m,n) Thrust coefficient 
   x        (1,n) Ratio of exhaust pressure to chamber pressure

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