Can you find the orbital velocity of a planet which a satellite has to obtain in order to revolve around the planet with this formula:(adsbygoogle = window.adsbygoogle || []).push({});

v = [tex]\sqrt{\frac{Gm_E}{r_E}}[/tex]

G = gravitational constant 6.67*10^{-11}

m_{E}= Mass of a planet

r_{E}= the radius of the orbit

r_{E}= h + r

h = height of the orbit

r = the radius of a plant from the center of the planet to its surface

Lets see, if you want to find the orbital velocity that a satellite has to get in order to orbit the Earth in Low Earth Orbit (346.9 km).

m_{E}= 5.98*10^{24}kg

r_{E}= h + r

h = 346,900 meters (346.9 km)

r = 6.38*10^{6}meters

v = [tex]\sqrt{\frac{(6.67*10^-^1^1)(5.98*10^2^4 kg))}{6,726,900}}[/tex]

v = 7,700.27 m/s

In order to obtain an orbit at an altitude of 346.9 km you will need to get a velocity of 7,700.27 m/s. Is this right, if not please correct me. Thank you for your time.

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# Orbital Speed of a Satellite

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