Posted by Ruth on .
1)What must be the orbital speed of a satellite in a circular orbit 740 above the surface of the earth?
2)What is the period of revolution of a satellite with mass that orbits the earth in a circular path of radius 8000 (about 1630 above the surface of the earth)?

PHYSIC 
drwls,
You must provide units with your numbers. You should have learned that by now

PHYSIC 
tchrwill,
Since 8000  1630 = 6370, the radius of the earth in km, I believe I am on safe ground assuming that you mean "740km" above the earth in your first question.
The velocity required to maintain a circular orbit derives from Vc = sqrt(µ/r) where Vc = the velocity in m/s, µ = the earth's gravitational constant, 3.9863x10^14 m^3/sc^2 and r = the orbital radius in meters.
Therefore,
Vc = sqrt[3.9863x10^14/(6370+740)1000]
The period of a particular orbit derives from
T = 2(Pi)sqrt(r^3/µ)
I'll let you complete this one.