Author name: Bhagiya Prasad

Inlet density, denoted as 𝜌0, refers to the density of the fluid (typically a gas) entering a system or device at its inlet point. It represents the mass of the fluid per unit volume at the initial point of entry.  Inlet density (𝜌0) in kg/m^3 Inlet pressure (p0) in N/m^2 Specific gas constant (R) in […]

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. Thrust is a critical parameter for rocket performance and is a result of Newton’s third law of motion: “For

The ratio of the area at the throat to the area at sonic flow, denoted as At/A*, is a key parameter in fluid dynamics that quantifies the change in cross-sectional area as the flow transitions from subsonic to supersonic conditions in a nozzle or flow passage.  Ratio of area at the throat to the area

The “static temperature at the exit where the flow is supersonic,” denoted as Te, refers to the temperature of the fluid at the exit of a nozzle or flow passage when the flow velocity exceeds the speed of sound and enters supersonic conditions. Static temperature refers to the temperature of the fluid at rest (not

The “static pressure at the exit where the flow is supersonic,” denoted as pe, refers to the pressure of the fluid at the exit of a nozzle or flow passage when the flow velocity exceeds the speed of sound. In other words, it’s the pressure at the point where the flow has transitioned into supersonic

The “static temperature at the throat where the flow is sonic,” denoted as Tt, refers to the temperature of the fluid at the narrowest cross-sectional area of a nozzle or flow passage where the flow velocity has reached the speed of sound. This condition is often referred to as “sonic flow” or “choked flow.”  Static

The “static pressure at the throat where the flow is sonic,” denoted as pt, refers to the pressure of the fluid at the narrowest cross-sectional area of a nozzle or flow passage where the flow velocity has reached the speed of sound. This condition is often referred to as “sonic flow” or “choked flow.” Ratio

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.  Mass flow rate (ṁ) in kg/s Density of sonic flow at throat (𝜌*) in kg/m^3 Velocity of sonic flow at

Mass flow rate during sonic flow at the throat refers to the rate at which mass is passing through the narrowest cross-sectional area of a convergent-divergent nozzle when the fluid velocity reaches the speed of sound.  Density of sonic flow at throat (𝜌*) in kg/m^3 Velocity of sonic flow at throat (u*) in m/s Cross-sectional

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.  Density at throat (𝜌t) in kg/m^3 Velocity at throat (ut) in m/s Cross-sectional area at throat (At) in m^2 Mass