h = 600 km = 6.0×10^5 m, R = 6.37×10^6 m, g = 9.8 m/s²
Orbital radius: r = R + h = 6.37e6 + 6e5 = 6.97e6 m
Orbital speed: v = sqrt(g*R² / r) = sqrt(9.8*6.37e6² / 6.97e6)
v = sqrt(3.977e14 / 6.97e6) = sqrt5.71e7 = 7556 m/s

First, calculate the orbital radius (r), which is the distance from the center of the Earth to the satellite:
r = R_E + h
r = 6.37 × 10^6 m + 6.00 × 10^5 m
r = 6.37 × 10^6 m + 0.60 × 10^6 m
r = 6.97 × 10^6 m
The formula for orbital speed (v) is:
v = sqrt((G * M_E) / r)
Substitute the values:
v = sqrt((6.674 × 10^-11 N·m²/kg² * 5.972 × 10^24 kg) / 6.97 × 10^6 m)
v = sqrt((3.981 × 10^14 N·m²/kg) / 6.97 × 10^6 m)
v = sqrt(5.711 × 10^7 m²/s²)
v 7557 m/s
Therefore, the orbital speed of the satellite is approximately 7557 m/s or 7.56 km/s.