Mechanical Energy- Orbit

1. The problem statement, all variables and given/known data

What is the total mechanical energy of a 380kg satellite in a circular orbit 3.0 Earth radii above the surface?





2. Relevant equations

W= E₂- E₁



E= 1/2 mv²- [itex]\frac{GmM}{r}[/itex]





3. The attempt at a solution



I'm not sure if the equations above are suitable to solve this or I just don't understand how to start the question.

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