Rocket Equation
Calculate rocket performance using the Tsiolkovsky rocket equation. This equation relates the change in velocity (Δv) with the effective exhaust velocity (ve) or specific impulse (Isp) and the mass ratio of the rocket.
Delta-v
2.0392 km/s
2039.24 m/s
Mass ratio
2.000:1
50.00% propellant
Initial mass
10000.00 kg
final 5000.00 kg
Exhaust velocity
2941.99 m/s
Isp 300.0 s
Ideal burn picture
The rocket starts wet, throws propellant backward through the engine, and keeps the remaining vehicle moving faster.
Delta-v 2.039 km/s
Before burn
10,000 kg wet
Vehicle plus propellant at ignition.
Expelled propellant
5,000 kg
Exhaust leaves backward at 2,942 m/s.
After burn
5,000 kg dry
Remaining vehicle has gained 2.039 km/s ideal delta-v.
Propellant fraction
50.0%
share of wet mass thrown backward
Exhaust velocity
2,942 m/s
from 300.0 s Isp
Log term
0.693
natural log of wet-to-dry mass
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