Inputs
Formulas
r = (R + h)v = √( μ / r )T = 2π √( r³ / μ )ε = - μ / (2r)a = v² / r = μ / r²
Units: R and h in meters when used inside formulas. Inputs above are in km for radii and m³/s² for μ.
Results
r = 6,771.000 km| Orbital speed | 7,672.599 m/s (7.673 km/s) |
|---|---|
| Orbital period | 5,544.855 s (1 h 32 m 24.855 s) |
| Specific orbital energy | -29,434,385.010 J/kg |
| Centripetal acceleration | 8.694 m/s² |
| Gravity at altitude | 8.694 m/s² |
| Orbit circumference | 42,543.448 km |
| Orbits per day | 15.582 |
Assumptions
- Point-mass gravity with constant μ at the entered altitude.
- No perturbations (oblateness J2, drag, third bodies, thrust) are modeled.
- Inputs can be adjusted to analyze other planets or custom scenarios.
FAQs
It is the square root of μ divided by the orbital radius r where r equals planet radius plus altitude. Enter μ and radii and the tool computes v.
Use μ ≈ 3.986004418×10^14 m³/s². This constant equals G times the mass of Earth and is widely used for orbital mechanics.
No. The model is ideal two body motion. Real satellites at 400 km experience drag that slowly reduces energy and requires periodic reboost.
For a stable circular orbit the inward gravitational acceleration exactly matches v²∕r which keeps the satellite moving along a circular path.
Yes. Replace μ with the body specific value and set the correct radius. The equations remain valid for any spherical body with a known μ.
Approximately 7.67 km/s. The exact number depends on the chosen constants. This tool reports both m/s and km/s precisely to your selected decimals.
About fifteen orbits per day. The value derives from 86400 seconds divided by the computed orbital period for the given r and μ.