How do you calculate the altitude of a satellite in geosynchronous orbit?

Using the equation for gravitational force and the equation for centripetal force?

So... m(v)^2/r = G(m1m2/d^2)

We started off in class with m(2*pi*r/86400 s)^2/r = G(m1m2/d^2)

What now? Thanks.
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