Mass Flow Rate in Turbojet given Thrust Calculator

✖Net Thrust of Turbojet denotes the total thrust or forward force exerted by the engine to propel an aircraft forward.ⓘ Net Thrust of Turbojet [T]			+10% -10%
✖Nozzle Exit Area refers to the cross-sectional area at the exit of a nozzle.ⓘ Nozzle Exit Area [A_e]			+10% -10%
✖Nozzle Exit Pressure refers to the pressure at the exit of a nozzle or exhaust of a system.ⓘ Nozzle Exit Pressure [p_e]			+10% -10%
✖Ambient Pressure refers to the pressure of the surrounding environment, typically measured relative to a vacuum.ⓘ Ambient Pressure [p_∞]			+10% -10%
✖Exit Velocity refers to the speed at which gases expand at the exit of nozzle of a turbojet engine.ⓘ Exit Velocity [V_e]			+10% -10%
✖Flight Speed refers to the velocity at which an aircraft travel through the air.ⓘ Flight Speed [V]			+10% -10%
✖Fuel Air Ratio signifies the proportion of fuel mixed with air in a combustion system.ⓘ Fuel Air Ratio [f]			+10% -10%

✖Mass Flow Rate Turbojet represents the amount of air entering a turbojet engine per unit time.ⓘ Mass Flow Rate in Turbojet given Thrust [m_a]

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Mass Flow Rate in Turbojet given Thrust Solution

STEP 0: Pre-Calculation Summary

Formula Used

Mass Flow Rate Turbojet = (Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/((Exit Velocity-Flight Speed)*(1+Fuel Air Ratio))
m_a = (T-A_e*(p_e-p_∞))/((V_e-V)*(1+f))
This formula uses 8 Variables

Variables Used

Mass Flow Rate Turbojet - (Measured in Kilogram per Second) - Mass Flow Rate Turbojet represents the amount of air entering a turbojet engine per unit time.
Net Thrust of Turbojet - (Measured in Newton) - Net Thrust of Turbojet denotes the total thrust or forward force exerted by the engine to propel an aircraft forward.
Nozzle Exit Area - (Measured in Square Meter) - Nozzle Exit Area refers to the cross-sectional area at the exit of a nozzle.
Nozzle Exit Pressure - (Measured in Pascal) - Nozzle Exit Pressure refers to the pressure at the exit of a nozzle or exhaust of a system.
Ambient Pressure - (Measured in Pascal) - Ambient Pressure refers to the pressure of the surrounding environment, typically measured relative to a vacuum.
Exit Velocity - (Measured in Meter per Second) - Exit Velocity refers to the speed at which gases expand at the exit of nozzle of a turbojet engine.
Flight Speed - (Measured in Meter per Second) - Flight Speed refers to the velocity at which an aircraft travel through the air.
Fuel Air Ratio - Fuel Air Ratio signifies the proportion of fuel mixed with air in a combustion system.

STEP 1: Convert Input(s) to Base Unit

Net Thrust of Turbojet: 469 Newton --> 469 Newton No Conversion Required
Nozzle Exit Area: 0.0589 Square Meter --> 0.0589 Square Meter No Conversion Required
Nozzle Exit Pressure: 982 Pascal --> 982 Pascal No Conversion Required
Ambient Pressure: 101 Pascal --> 101 Pascal No Conversion Required
Exit Velocity: 213 Meter per Second --> 213 Meter per Second No Conversion Required
Flight Speed: 130 Meter per Second --> 130 Meter per Second No Conversion Required
Fuel Air Ratio: 0.008 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

m_a = (T-A_e*(p_e-p_∞))/((V_e-V)*(1+f)) --> (469-0.0589*(982-101))/((213-130)*(1+0.008))

Evaluating ... ...

m_a = 4.98552663033085

STEP 3: Convert Result to Output's Unit

4.98552663033085 Kilogram per Second --> No Conversion Required

FINAL ANSWER

4.98552663033085 ≈ 4.985527 Kilogram per Second <-- Mass Flow Rate Turbojet

(Calculation completed in 00.004 seconds)

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Created by Himanshu Sharma

National Institute of Technology, Hamirpur (NITH), Himachal Pradesh

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National Institute Of Technology (NIT), Hamirpur

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< Turbojets Calculators

Nozzle Exit Area in Turbojet

LaTeX Go Nozzle Exit Area = (Net Thrust of Turbojet-Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*(Exit Velocity-Flight Speed))/(Nozzle Exit Pressure-Ambient Pressure)

Turbojet Gross Thrust

LaTeX Go Gross Thrust of Turbojet = Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*Exit Velocity+(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area

Mass Flow Rate of Exhaust Gases given Fuel Air Ratio

LaTeX Go Total Mass Flow Rate Turbojet = Mass Flow Rate Turbojet*(1+Fuel Air Ratio)

Mass Flow Rate of Exhaust Gases

LaTeX Go Total Mass Flow Rate Turbojet = Mass Flow Rate Turbojet+Fuel Flow Rate

Mass Flow Rate in Turbojet given Thrust Formula

LaTeX Go

Mass Flow Rate Turbojet = (Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/((Exit Velocity-Flight Speed)*(1+Fuel Air Ratio))
m_a = (T-A_e*(p_e-p_∞))/((V_e-V)*(1+f))

What is mass flow rate?

In physics and engineering, mass flow rate is the mass of a substance which passes per unit of time. Its unit is kilogram per second in SI units, and slug per second or pound per second in US customary units.

How to Calculate Mass Flow Rate in Turbojet given Thrust?

Mass Flow Rate in Turbojet given Thrust calculator uses Mass Flow Rate Turbojet = (Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/((Exit Velocity-Flight Speed)*(1+Fuel Air Ratio)) to calculate the Mass Flow Rate Turbojet, Mass Flow Rate in Turbojet given Thrust is a measure of the rate at which mass is flowing through a turbojet engine, which is essential for evaluating the engine's performance and efficiency. It is a critical parameter in aerospace engineering, as it affects the overall thrust produced by the engine and its fuel consumption. Mass Flow Rate Turbojet is denoted by m_a symbol.

How to calculate Mass Flow Rate in Turbojet given Thrust using this online calculator? To use this online calculator for Mass Flow Rate in Turbojet given Thrust, enter Net Thrust of Turbojet (T), Nozzle Exit Area (A_e), Nozzle Exit Pressure (p_e), Ambient Pressure (p_∞), Exit Velocity (V_e), Flight Speed (V) & Fuel Air Ratio (f) and hit the calculate button. Here is how the Mass Flow Rate in Turbojet given Thrust calculation can be explained with given input values -> 413.7987 = (469-0.0589*(982-101))/((213-130)*(1+0.008)).

FAQ

What is Mass Flow Rate in Turbojet given Thrust?

Mass Flow Rate in Turbojet given Thrust is a measure of the rate at which mass is flowing through a turbojet engine, which is essential for evaluating the engine's performance and efficiency. It is a critical parameter in aerospace engineering, as it affects the overall thrust produced by the engine and its fuel consumption and is represented as m_a = (T-A_e*(p_e-p_∞))/((V_e-V)*(1+f)) or Mass Flow Rate Turbojet = (Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/((Exit Velocity-Flight Speed)*(1+Fuel Air Ratio)). Net Thrust of Turbojet denotes the total thrust or forward force exerted by the engine to propel an aircraft forward, Nozzle Exit Area refers to the cross-sectional area at the exit of a nozzle, Nozzle Exit Pressure refers to the pressure at the exit of a nozzle or exhaust of a system, Ambient Pressure refers to the pressure of the surrounding environment, typically measured relative to a vacuum, Exit Velocity refers to the speed at which gases expand at the exit of nozzle of a turbojet engine, Flight Speed refers to the velocity at which an aircraft travel through the air & Fuel Air Ratio signifies the proportion of fuel mixed with air in a combustion system.

How to calculate Mass Flow Rate in Turbojet given Thrust?

Mass Flow Rate in Turbojet given Thrust is a measure of the rate at which mass is flowing through a turbojet engine, which is essential for evaluating the engine's performance and efficiency. It is a critical parameter in aerospace engineering, as it affects the overall thrust produced by the engine and its fuel consumption is calculated using Mass Flow Rate Turbojet = (Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/((Exit Velocity-Flight Speed)*(1+Fuel Air Ratio)). To calculate Mass Flow Rate in Turbojet given Thrust, you need Net Thrust of Turbojet (T), Nozzle Exit Area (A_e), Nozzle Exit Pressure (p_e), Ambient Pressure (p_∞), Exit Velocity (V_e), Flight Speed (V) & Fuel Air Ratio (f). With our tool, you need to enter the respective value for Net Thrust of Turbojet, Nozzle Exit Area, Nozzle Exit Pressure, Ambient Pressure, Exit Velocity, Flight Speed & Fuel Air Ratio and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Mass Flow Rate Turbojet?

In this formula, Mass Flow Rate Turbojet uses Net Thrust of Turbojet, Nozzle Exit Area, Nozzle Exit Pressure, Ambient Pressure, Exit Velocity, Flight Speed & Fuel Air Ratio. We can use 1 other way(s) to calculate the same, which is/are as follows -

Mass Flow Rate Turbojet = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/((1+Fuel Air Ratio)*Exit Velocity)

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