the corresponding parameter.
</p>
<p>
    The throat Mach number is then determined using an iterative process.
    Initial, subsonic guesses for the variables <i>Mth<sub>0</sub></i> and <i>Mth<sub>1</sub></i>
    are made arbitrarily, and the initial guesses for the corresponding temperature
    and area ratios are determined by using the following equations:

    $$\textit{Tcr_o_T}th_0 = \frac{2}{\gamma+1}*[1+0.5*(\gamma-1)*Mth_0^2]$$
    $$\textit{Ath_o_A}cr_0 = \frac{\textit{Tcr_o_T}th_0^\frac{\gamma+1}