ThrustToAStar:

Path: Propulsion/Rocket

% Computes throat area (A*) for a given thrust
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   Form:
   aStar = ThrustToAStar( g, thrust, p0, pA, e )
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   ------
   Inputs
   ------
   fuel         (1,:)  Fuel type, ex. 'air','nitrogen'
   thrust       (1,1)  Thrust level (N)
   p0           (1,1)	Chamber pressure (N/m^2)
   pA           (1,1)  Ambient pressure (N/m^2)
   e            (1,1)  Area ratio (exit area/throat area)

   -------
   Outputs
   -------
   aStar        (1,1)  Throat area (m^2)

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  See also GasProperties, TCoeff
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Children:

Propulsion: Gas/GasProperties
Propulsion: Rocket/TCoeff

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