for a satellite at a height of 500 miles at what speed must the satellite be traveling to achieve a circular orbit?
V^2/R = g*(Re/R)^2
g = 32.2 ft/s^2
Re = earth radius = 3960 miles
R = orbit radius = 4460 miles = 2.355*10^7 feet
Re/R = 0.888
Solve for V in ft/s
V = 1.349*10^4 ft/s