A satellite is in circular orbit above the Earth at an altitude of 2000 km. What is the orbital speed of the satellite? what is the equation i need to use

GM/(Re +h)^2 = V^2/(Re + h)

or
G M = V^2*(Re + h)

Solve for V

G = universal constant of gravity
Re = Earth radius = 6370 km
h = 2000 km
M = Earth's mass

I did that and I am still getting the wrong answers, do I have to convert anything?

Re and h should be in meters if G is in N*m^2/kg^2

M must be in kg. Are you sure you used the correct values for G and M?

You will get the answer in m/s if you do it right.

To calculate the orbital speed of a satellite, you can use the equation for circular motion:

Orbital speed (v) = √(G * M / r)

Where:
- v is the orbital speed,
- G is the gravitational constant (approximately 6.67 × 10^-11 N*m^2/kg^2),
- M is the mass of the Earth (approximately 5.97 × 10^24 kg),
- r is the radius of the satellite's orbit, which is the sum of the Earth's radius and the altitude of the satellite.

In this case, the altitude of the satellite is given as 2000 km, which is equivalent to 2000000 meters. The radius of the satellite's orbit is calculated as the sum of the Earth's radius (6371000 meters) and the altitude:

r = Earth's radius + altitude
= 6371000 m + 2000000 m
= 8371000 m

Now, substitute the values into the equation:

v = √(G * M / r)
= √((6.67 × 10^-11 N*m^2/kg^2) * (5.97 × 10^24 kg) / 8371000 m)

Evaluating this equation will give you the orbital speed of the satellite.