TCoeff:

Path: Propulsion/Rocket

% 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.

--------------------------------------------------------------------------
   Form:
   [cF, x] = TCoeff( g, e, p )
--------------------------------------------------------------------------

   ------
   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

--------------------------------------------------------------------------

Children:

Common: General/DeBlankLT
Common: Graphics/Mesh2
Common: Graphics/NewFig
Common: Graphics/PltStyle
Common: Graphics/XLabelS
Common: Graphics/YLabelS
Common: Graphics/ZLabelS

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