Rocket assistant designerEnter 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 :

Hydrogen UDMH Kerosen (RP-1)

Enter oxidizer type

Oxygen Nitrous Tetroxyd (N2O4) Fluor

Choose your geometry of combustion chamber :

Sphere Cylinder

Nozzle type :

bell nozzle conical (1/2 angle) aerospike

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

Overalltemperature

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