Angular/Linear Velocity Problem

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To solve the problem of a satellite's linear velocity in orbit, the key equations involve the relationship between linear and angular velocity, expressed as v = ωr. The angular velocity of the Earth can be calculated using the formula ω = 2π/T, where T is the period of Earth's rotation (24 hours). The satellite's altitude of 3000 km above the Earth's surface means its distance from the center of the Earth is 9400 km (6400 km radius + 3000 km altitude). By determining the distance the satellite travels in one orbit and the time taken, the linear velocity can be directly calculated. Understanding these relationships is crucial for accurately estimating the satellite's linear velocity.
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Homework Statement


A satellite is orbiting at 3000Km above the equator so that's it's angular velocity is the same as Earths. Assuming the Earth to be a sphere of radius 6400Km, estimate the linear velocity of the satellite relative to the centre of the Earth given that the Earth rotates exactly once every 24 hours.


Homework Equations





The Attempt at a Solution


This is a problem someone asked me to help with but it's been so long since i was in college I'm finding it hard to remember what equations i should be going for.

Can anyone give me the equations i would need to solve this problem?
 
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how do i use the period of the Earth to find out the angular velocity?
 
controlfreaks said:
how do i use the period of the Earth to find out the angular velocity?
How many radians does the Earth turn through in one period?

You can also figure out the linear velocity directly, without bothering with angular velocity. What distance does the satellite travel in one orbit? How much time does it take?
 
so would it be that the angular velocity is equal to 2pi divided by time taken?
 
yuP =)
 
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