A question on centripetal acceleration

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To estimate the time it takes for a satellite in near-Earth orbit to complete one revolution, centripetal acceleration must be calculated using the formula a = v^2/r, where r is the Earth's radius of approximately 6400 km. The gravitational force acting on the satellite is equal to its weight, mg, which provides the necessary centripetal force. To find the satellite's velocity, the relationship between gravitational force and centripetal force can be utilized, leading to the equation v = √(g*r), where g is the acceleration due to gravity. Once the velocity is determined, the orbital period can be calculated using the formula T = 2πr/v. This approach allows for an accurate estimation of the satellite's orbital time.
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Estimate the time it takes a satellite in “near-earth” orbit to go once around the earth. To do this, assume that it is close enough to the earth’s surface that the gravitational force acting on it is about equal to its weight on earth, mg. Proceed as follows:

a. Find the centripetal acceleration the satellite must experience in its circular orbit.

a=v^2/r
Since we're talking about the earth, I'm assuming that we use the Earth's radius, 6400km. However, I have no idea where to get the velocity of this satellite from.
 
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What is the centripetal force acting on the satellite? Can you use this to find the velocity of the satellite?
 
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