Effective Exhaust Velocity
Convert rocket specific impulse into effective exhaust velocity, mass flow, and thrust power.
Exhaust velocity
3.24 km/s
3,236 m/s from Isp x g0
Mass flow
30.90 kg/s
100.0 kN divided by effective velocity
Jet power
161.81 MW
ideal kinetic power rate in the exhaust stream
Specific impulse to velocity
Specific impulse in seconds becomes an equivalent exhaust velocity when multiplied by standard gravity.
3.24 km/s effective
NASA relation
c = Isp g0
Effective velocity
3,236 m/s / 3.24 km/s
Mass-flow consequence
30.90 kg/s for 100.0 kN
higher effective velocity lowers propellant flow
Kinetic power check
161.81 MW
0.5 mdot c squared, before real losses
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