A wide aerospace fuselage panel has a through-thickness central crack of length $2a = 16\text{ mm}$ (half-crack $a = 8\text{ mm} = 0.008\text{ m}$). The panel is subjected to uniform tensile stress $\sigma = 250\text{ MPa}$. Taking the geometric correction factor $Y = 1.0$, what is the stress intensity factor $K_I$ in $\text{MPa}\sqrt{\text{m}}$? (Take $\pi \approx 3.1416$, round to two decimal places).