Asked by John Dosley

The orbital velocity of a satellite is given by v=√GM/R+h, where G= 6.67*10^-11 Nm^2kg^2, is the Universal Gravitational Constant, M=6*10^24 kg, is the mass of Earth, R=6.38*10^3 km, the orbit of the satellite, and h is artificial satellite above the surface of Earth. Use the information to find the orbital velocity of an artificial satellite orbiting Earth at a height of 2500km.

9 years ago

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