Rocket Nozzle Design

1.2

γ

(Ratio of Specific Heats)

1

2

361

J/kg.K

 

R

100

500

(Specific Gas Constant)

_

1.268

MPa

 

Chamber Pressure

1

25

2103

°K

 

Chamber Temperature

1500

4000

0.002

m

 

Nozzle Throat

Diameter

0.001

1.0

90

 

Combustion

85

90

%

 

Nozzle

98

Efficiency

1.01325

kPa

0

Exhaust Pressure

& Equivalent Altitude

0km

(sea lvl)

100km

(edge of space)

1.01325

kPa

0

Ambient Pressure

& Equivalent Altitude

0km

(sea lvl)

100km

(edge of space)

This code calculates ideal rocket nozzle geometry

for input parameters describing the combustion chamber environment and desired exhaust characteristics under isentropic conditions.

Vehicle structures and Delta-V

budgets are configured

and mapped below.

Engine Preset

arrow&v

Nozzle Length

Result

m

Exit Diameter

Result

m

Expansion Ratio

Result

NOZZLE GEOMETRY

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)

arrow&v
arrow&v

1

 

Number of

Engines

1

9

I

Result

SP

(Specific Impulse)

361

 

Vehicle
Fuel Mass

1

3000

361

 

Vehicle
Payload Mass

1

3000

s

VEHICLE STRUCTURE 

361

 

Engine
Unit Mass

1

1000

arrow&v

DELTA-V BUDGET MAP

Click a starting point on the Delta-V map to predict the range of paths achievable by the above rocket engine and vehicle configuration, travelling between some of the nearer parts of the Solar System.

Default start: Earth.

Note: This Delta-V budget map does not take rocket-staging into account, nor does it facilitate boosters (hence why some of the presets fail to lift off from earth when in reality they are able to).

The calculation also freezes the above engine ISP at its design ambient pressure/altitude, so atmospheres of destinations/origins don't alter the engine performance like they would in real life. 

It also assumes that at each subsequent waypoint after the original launch point, the vehicle has a sufficient thrust to weight ratio (TWR) to lift off again.

Total Thrust

Result

N

TWR

Result

Thrust to Weight Ratio

V

Result

Impulse per unit mass

(space-faring "budget")

km/s

progress toward waypoint

one-way trip between

waypoints achievable

round trip between

waypoints achievable

Categories

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