1. The problem statement, all variables and given/known data a. What is the tangential velocity of a satellite in a circular orbit 300km above the surface of the Earth? 2. Relevant equations Velocity of a satellite= v^2= G (Me/r) 3. 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?.