Air \((\gamma=1.4)\) flows isentropically through a convergent-divergent nozzle. At a certain section, the Mach number is \(1.0\) (at the throat). If the stagnation temperature is \(720\ \text{K}\), find the static temperature at the throat.
Show Hint
For isentropic compressible flow,
\[
\boxed{
\frac{T_0}{T}
=
1+\frac{\gamma-1}{2}M^2.
}
\]
At the nozzle throat,
\[
\boxed{
M=1.
}
\]