What linear speed must an Earth satellite have to be in a circular orbit at an altitude of 186 km? What is the period of revolution?

So GMm/r^2 = mv^2/r and I know that I need to solve for v but what do I use for the mass of the satellite?

Do I just plug in values for G, M, m and r (which equals 6.37e6 + 186e3) and solve for v that way???

got it.