a. What is the tangential velocity of a satellite in a circular orbit 300km above the surface of the Earth?
Velocity of a satellite= v^2= G (Me/r)
The Attempt at a Solution
V^2= 6.67E-11 (5.98E24/6.37E6)
I calculated this and my answer proved incorrect. How do I incorporate the "300 km above earths surface" into this equation?.