Rocket Burn Time
Calculate propellant mass flow, burn time, and total impulse from thrust, Isp, and propellant mass.
Burn time
627.63 s
10.46 min at steady thrust
Mass flow
143.40 kg/s
from thrust / effective exhaust velocity
Total impulse
282.43 MN s
3.14 km/s effective exhaust
Propellant depletion timeline
Specific impulse sets the mass flow needed for the requested thrust; propellant mass then sets burn duration.
10.46 min burn
Mass-flow link
mdot = T / (Isp g0)
Burn duration
627.6 s / 10.46 min
90,000 kg propellant
Total impulse
282.43 MN s
equal to thrust times burn time
Specific impulse
320 s to 3.14 km/s
Open Source and Easy to Use Elsewhere
This tool is open source and the underlying logic is fully transparent. You can inspect the code, understand the calculations, and contribute improvements. If you want to use the tool in your own website, course page, or learning platform, you can also embed it directly and start from a ready-made iframe setup for this exact tool.
Open source: review the implementation and see how the results are produced.
Embeddable: preview this tool, copy the iframe, and use it in your own site or LMS.