Rocket Nozzle Design

Engine Preset

Nozzle Length

Result

m

Exit Diameter

Result

m

This design code calculates ideal rocket nozzle geometry for given input parameters describing

the combustion chamber environment and

desired exhaust pressure.

Expansion Ratio

Result

Exhaust Mach

Result

Pressure Ratio

Result

Ex. Temperature

Result

°K

Mass Flow Rate

Result

kg/s

Thrust

Result

N

I

Result

SP

s

(Specific Impulse)

1

Number of

Engines

1

9

I

Result

SP

(Specific Impulse)

361

Vehicle
Fuel Mass

1

3000

361

Vehicle
Payload Mass

1

3000

s

361

Engine
Unit Mass

1

1000

Total Thrust

Result

N

TWR

Result

Thrust to Weight Ratio

∆V Mission Map:

Choose starting point

∆V

Result

km/s

Impulse per unit mass

(space-faring "budget")