Cross-Sectional Area of a Exhaust for a Cold Gas Propulsion Rocket Nozzle Calculator

In the case of cold gas propulsion systems, the cross-sectional area of the exhaust nozzle is crucial for determining the flow characteristics and thrust generation. Cold gas propulsion involves the release of compressed gas (usually stored at high pressure) through a rocket nozzle to produce thrust.

For cold gas propulsion, where combustion is not involved, the design of the exhaust nozzle focuses on efficiently releasing the compressed gas to generate thrust.

The relationship between the cross-sectional areas and velocities at the throat and exit of a rocket nozzle can be described by the rocket equation:

A1​⋅V1​=A2​⋅V2​

where:

• A1​ and A2​ are the cross-sectional areas at the nozzle Throat and exit, respectively,
• V1​ and V2​ are the velocities at the nozzle Throat and exit, respectively.

which gives,

where,

• A1​ is the cross-sectional area of the nozzle at the throat,
• V1​ is the velocity of the exhaust gases at the throat,
• A2​ is the cross-sectional area of the nozzle at the exit,
• V2​ is the velocity of the exhaust gases at the nozzle exit.