Author name: Bhagiya Prasad

At,2 (Diffuser Throat Area): This is the cross-sectional area of the throat of the diffuser section of a propulsion system. The diffuser is the component responsible for slowing down and compressing incoming air or propellant flow before it enters the combustion chamber or nozzle. The area of the diffuser throat is an important parameter in […]

Mass flow through a rocket engine refers to the rate at which propellant material (usually a combination of fuel and oxidizer) is being consumed and expelled from the engine to produce thrust. In a rocket engine, propellant is burned in a combustion chamber to generate high-speed exhaust gases. These gases are expelled through a nozzle

The mass flow through the diffuser at station two refers to the rate at which mass of a fluid flows through a specific point or location (station two) within the diffuser section of a flow passage. A diffuser is a component in fluid systems designed to slow down and increase the pressure of a flowing

The mass flow through the nozzle at station one refers to the rate at which mass of a fluid flows through a specific point or location (station one) within the nozzle or flow passage. It’s a measure of how much mass of the fluid passes through a cross-sectional area per unit of time.  ṁ₁: Mass

ṁ: This symbol represents the mass flow rate, which is the amount of mass passing through a given cross-sectional area per unit time. It’s typically measured in kilograms per second (kg/s) or other mass/time units.  ṁ: Mass flow rate (kg/s) 𝜌*: Density of the fluid  (kg/m³) u: Velocity (speed of sound)  (m/s) A*: Cross-sectional area

Thrust (T) is the force generated by the expulsion of exhaust gases from a rocket engine’s nozzle. It’s the force that propels the rocket forward in the opposite direction to the exhaust gases being expelled backward.  NOTE: When pe = p∞, the pressure term drops out, we get ṁ: Mass flow rate of the exhaust

The velocity at the exit, denoted as ue, refers to the speed at which the fluid exits a nozzle or flow passage. This parameter is crucial in fluid dynamics and aerodynamics, as it determines the final velocity of the fluid after it has undergone acceleration or expansion within the nozzle.  ue: Velocity at the exit

The velocity at the exit, denoted as ue, refers to the speed at which the fluid exits a nozzle or flow passage. This parameter is crucial in fluid dynamics and aerodynamics, as it determines the final velocity of the fluid after it has undergone acceleration or expansion within the nozzle.  Velocity at the exit (ue)

The speed of sound at the exit, denoted as ae, refers to the velocity at which pressure waves or disturbances travel through a fluid medium at the exit of a nozzle or flow passage. It represents the local speed of sound at the point where the fluid flow reaches its maximum speed.  Specific heat ratio

The speed of sound at sonic flow, denoted as a*, refers to the velocity at which pressure waves propagate through a fluid medium when the flow velocity of the fluid matches the local speed of sound. In other words, it’s the speed at which disturbances in pressure, density, and temperature travel through the fluid. At