qrt{2*Cp*g*Jc*(Ttmfp_{In} - Tth)}$$

    The flow density at the throat is determined by:

    $$&rho;_{th} = \frac{Pth*144}{R*Jc*Tth}$$

    in which the 144 is used to convert from PSI to PSF.
</p>
<p>
    The flow at the throat is determined by the following equation, in which
    the 144 is again used to convert to the proper units.

    $$Wth = \frac{&rho;_{th}*Ath*Vth}{144}$$

    The Mach number at the throat is verified and recalculated by the following:

    $$Mth = \frac{Vth}{\sqrt{\gamma*R*g*Jc*T