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

Satellites are placed in a circular orbit that is 1.20 × 106 m above the surface of the earth. What is the magnitude of the acceleration due to gravity at this distance?

**2. Relevant equations**

My book is saying that the relevant equations are:

W = G((M_{E} *m*)/r^{2})

W = *m*g

**3. The attempt at a solution**

After looking at this post, I tried the formula g = MG/r^2. (M being the mass of the Earth)

g = ((6.67 x 10^-11)(5.97 x 10^24))/((1.20 x 10^6)^2)

This^ yielded 276.53 m/s^2, which is apparently wrong.

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