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

Altitude

 

 

Real speed

Net Propulsion
Force

Max Air Drag during fly.

 

 

Ratio Dry On
Full

Thrust to weight
ratio

Remaining structural mass ratio

Motor mass



Threat on structure

POGO effect

Overall
temperature



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