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

In a cold gas propulsion system, the propellant is stored in gaseous form, and there is typically no combustion involved. The cold gas is expelled through a rocket nozzle to generate thrust. The design of the throat in a cold gas rocket nozzle is critical for controlling the flow and optimizing the exhaust velocity.

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,

In this equation:

• 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.