Circular Orbital Velocity

\[v=\sqrt{\frac{\mu}{r}}\]

Variables

vcircular orbital velocity (m/s)

mu[μ]standard gravitational parameter (m³/s²)

rorbital radius from the central body's center (m)

The Circular Orbital Velocity formula calculates the speed required for a spacecraft or satellite to maintain a circular orbit around a central body.

It is a fundamental equation in orbital mechanics and astrodynamics.

Use this formula when calculating the orbital speed of satellites, spacecraft, moons, or objects moving in circular or nearly circular orbits.

It is useful for mission design, satellite deployment, orbital analysis, and aerospace engineering education.

A satellite orbits Earth with:

Orbital radius = 7.0×10^6 m

Earth gravitational parameter = 3.986×10^14 m³/s²

Formula:

v = √(μ / r)

Substitution:

v = √(3.986×10^14 / 7.0×10^6)

v = 7546 m/s

Result:

Circular orbital velocity = 7.55 km/s

Satellite orbit design

Spacecraft mission planning

Low Earth orbit calculations

Orbital mechanics education

Launch vehicle analysis

Astrodynamics