Rocket assistant designer

Enter the parameters of the rocket motor here :

Rocket Surface :

Total mass

Propellant mass

Ejected Mass per second

Number of stage

1 stage 2 stages

Simulation number of loop (seconds)

Enter fuel type :


Enter oxidizer type


Choose your geometry of combustion chamber :


Nozzle type : 


There are the results in meter (~1 yard), kg (for mass), Newton (10 N ~2 pounds) and second:


Theoretical speed

Full propulsion force




Real speed

Net Propulsion

Max Air Drag during fly.



Ratio Dry On

Thrust to weight

Remaining structural mass ratio

Motor mass

Threat on structure

POGO effect


Length of tanks

Chamber pressure

Chamber temperature

Gas speed in Comb. Chamber

Gas speed
in throat

Gas speed
in exhaust nozzle

Gas time while in Comb. Chamber

Location of burning front

Throat diameter

Volume of combustion chamber

Length of combustion chamber