Formula
| Escape velocity | v_e = √(2 G M / r) |
|---|---|
| G | 6.674 × 10⁻¹¹ N·m²/kg² |
| Circular orbit | v_c = √(G M / r) = v_e / √2 |
| Period | T = 2π √(r³ / G M) |
Escape velocities from surface
| Body | Surface v_e (km/s) |
|---|---|
| Moon | 2.38 |
| Mercury | 4.25 |
| Mars | 5.03 |
| Venus | 10.36 |
| Earth | 11.19 |
| Uranus | 21.4 |
| Neptune | 23.5 |
| Saturn | 35.5 |
| Jupiter | 59.5 |
| Sun (from surface) | 617.5 |
Earth-specific orbits
| LEO (200 km) | ~7.8 km/s orbital, ~11.0 km/s escape |
|---|---|
| GEO (35 786 km) | ~3.07 km/s orbital, ~4.35 km/s escape |
| Moon's orbit | ~1.02 km/s orbital |
Notes
- Escape velocity assumes no atmosphere, no propulsion during ascent, and ignores the planet's rotation.
- Launching eastward from near the equator subtracts Earth's rotation (~0.46 km/s at equator) from needed Δv.
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