Cross-Sectional Area of a Exhaust for a Liquid Propellent Rocket Nozzle Calculator

The cross-sectional area of the exhaust for a liquid propellant rocket nozzle is a critical parameter in the design of the rocket engine. For a liquid rocket engine, the design of the exhaust nozzle involves optimizing the expansion of the exhaust gases to achieve the desired exit velocity and thrust. The cross-sectional area of the exhaust at the exit is a key parameter in this design.

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.