Consider Kepler's equation regarding planetary orbits, given as M - E - esin(E), where M is the mean anomaly, E is the eccentric anomaly, and e measures eccentricity. Find the eccentric anomaly E when the mean anomaly M - - and the eccentricity of the orbit e - 0.81. Use Newton's method with initial approximation co - 3 to find x2, rounded to the nearest thousandth. Provide your answer below