Throat Exhaust Air Velocity For a Liquid Propellent Rocket Engine Calculator

In a liquid propellant rocket engine, the throat exhaust air velocity refers to the speed of the exhaust gases at the throat of the rocket nozzle. Liquid propellant rocket engines use liquid oxidizer and fuel, which are mixed and burned in the combustion chamber to produce high-speed exhaust gases.

In liquid propellant rocket engines, the design of the nozzle is crucial for optimizing thrust and efficiency. Engineers use these relationships to tailor the nozzle geometry for specific performance requirements. Detailed engineering analysis and simulations are typically conducted during the design process.

The continuity equation is based on the principle of mass conservation, and Bernoulli’s equation expresses the conservation of energy.

The continuity equation is given by:

A1​⋅V1​=A2​⋅V2​

where:

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

which gives

where,

• A₁ is the Cross-sectional area at the throat of the nozzle in m² 
• A₂ is the Cross-sectional area at the exit of the nozzle in m²
• V₁ is the Velocity of the exhaust gases at the throat in m/s
• V₂ is the Velocity of the exhaust gases at the nozzle exit in m/s