Posted by Charles on .
A satellite is in orbit 2500km above the surface of Earth. What is the velocity of the satellite in m/s?
Add 2500 m to the radius of the earth to get the distance R from the center. Make sure it is in meters.
Then use the equation GM/R^2 = V^2/R to get the velocity V
G is the universal constant of gravity and M is the mass of the Earth.
You will have some numbers to look up, but they should be easy to find.
The velocity required to maintain a circular orbit around the Earth may be computed from the following:
Vc = sqrt(µ/r)
where Vc is the circular orbital velocity in feet per second, µ (pronounced meuw as opposed to meow) is the gravitational constant of the earth, ~1.40766x10^16 ft.^3/sec.^2, and r is the distance from the center of the earth to the altitude in question in feet.
Using 3963 miles for the radius of the earth, the orbital velocity required for a 250 miles high circular orbit would be Vc = 1.40766x10^16/[(3963+250)x5280] = 1.40766x10^16/22,244,640 = 25,155 fps. (17,147 mph.) Since velocity is inversely proportional to r, the higher you go, the smaller the required orbital velocity.