The speed of a satellite in a circular orbit around the Earth can be calculated using the formula v = √(GM/r), where G is the gravitational constant, M is the mass of the Earth, and r is the distance from the center of the Earth to the satellite. For a satellite at a radius of 2.93 times the mean radius of the Earth, which is approximately 6.37 x 10^3 km, the total radius would be about 18,650 km. Substituting the values for G and M into the formula provides the orbital speed. The calculated speed is essential for maintaining a stable orbit. Understanding these calculations is crucial for satellite deployment and space missions.