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

The design of the exhaust for a solid propellant rocket nozzle is crucial for efficiently expelling the combustion gases and generating thrust. In a solid rocket motor, the propellant is in a solid state, and combustion occurs from the inside out, progressing radially from the center of the propellant grain toward the outer surface.

Unlike liquid rocket engines, solid rocket engines typically have a simpler design with a fixed geometry, and the exhaust nozzle may not have the same level of control as in other types of rocket engines. The design focuses on effectively channeling and directing the exhaust gases produced during combustion.

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.