A satellite is in an elliptical orbit around Earth with eccentricity $e = 0.5$ and orbital period $T = 8$ hours. Kepler's Equation relates the eccentric anomaly $E$ to the time $t$ from periapsis by $M = E - e \\sin(E)$, where $M = \\frac{2\\pi t}{T}$ is the mean anomaly. How many hours after passing periapsis does the satellite reach an eccentric anomaly of $E = \\frac{\\pi}{2}$?