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.

To calculate the velocity of a satellite in orbit, we can use the formula for the orbital velocity. The orbital velocity of a satellite can be determined by considering the gravitational force between the satellite and Earth.

The formula for the orbital velocity of a satellite is:

v = √(GM/R)

Where:
v = orbital velocity of the satellite
G = gravitational constant (6.67430 x 10^-11 m^3 kg^-1 s^-2)
M = mass of Earth (5.972 x 10^24 kg)
R = distance between the center of Earth and the satellite

In this case, the satellite is 2500km (or 2500000m) above the surface of the Earth. To calculate the distance between the center of the Earth and the satellite, we need to add the radius of the Earth to the altitude of the satellite.

The radius of the Earth is approximately 6371km (or 6371000m).

So, the distance between the center of the Earth and the satellite is:

R = radius of the Earth + altitude of the satellite
= 6371000 + 2500000
= 8871000m

Now, let's calculate the velocity of the satellite using the formula:

v = √(GM/R)
= √((6.67430 x 10^-11 m^3 kg^-1 s^-2) * (5.972 x 10^24 kg) / 8871000m)
≈ 7677.7 m/s

Therefore, the velocity of the satellite in m/s is approximately 7677.7 m/s.