ColdGas:

Path: Propulsion/Rocket

% Determines performance of a cold gas rocket.
 Thrust and mDot are functions of (p0,e). All inputs are mks.
 You need to compute p0 and t0 from the volume of the tank, mass of fuel
 and temperature.

 Type ColdGas for a demo.
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   Form:
   [thrust, iSP, rho, mDot] = ColdGas( s, aStar, p0, pA, t0, e )
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   ------
   Inputs
   ------
   s             (1,:) Gas to be used.
   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             (1,1) Area ratio

   -------
   Outputs
   -------
   thrust       (n,m)  Thrust level (N)
   iSP          (m)    Specific impulse (sec)
   rho          (n)    Gas density (kg/m^3)
   mDot         (n)    Mass flow (kg/sec)

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Children:

Common: Graphics/Plot2D
Propulsion: Gas/GasProperties
Propulsion: Rocket/IdealRkt

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