Net Thrust Produced by Turbojet Calculator

✖Mass Flow Rate Turbojet represents the amount of air entering a turbojet engine per unit time.ⓘ Mass Flow Rate Turbojet [m_a]			+10% -10%
✖Fuel Air Ratio signifies the proportion of fuel mixed with air in a combustion system.ⓘ Fuel Air Ratio [f]			+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%
✖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%

✖Net Thrust of Turbojet denotes the total thrust or forward force exerted by the engine to propel an aircraft forward.ⓘ Net Thrust Produced by Turbojet [T]

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Net Thrust Produced by Turbojet Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.
Fuel Air Ratio - Fuel Air Ratio signifies the proportion of fuel mixed with air in a combustion system.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Mass Flow Rate Turbojet: 5 Kilogram per Second --> 5 Kilogram per Second No Conversion Required
Fuel Air Ratio: 0.008 --> 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
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

STEP 2: Evaluate Formula

Substituting Input Values in Formula

T = m_a*(1+f)*(V_e-V)+A_e*(p_e-p_∞) --> 5*(1+0.008)*(213-130)+0.0589*(982-101)

Evaluating ... ...

T = 470.2109

STEP 3: Convert Result to Output's Unit

470.2109 Newton --> No Conversion Required

FINAL ANSWER

470.2109 Newton <-- Net Thrust of Turbojet

(Calculation completed in 00.007 seconds)

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Credits

Created by Himanshu Sharma

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

Himanshu Sharma has created this Calculator and 50+ more calculators!

Verified by Kartikay Pandit

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

Net Thrust Produced by Turbojet Formula

LaTeX Go

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

What is thrust?

Thrust is a reaction force described quantitatively by Newton's third law. When a system expels or accelerates mass in one direction, the accelerated mass will cause a force of equal magnitude but opposite direction to be applied to that system.

How to Calculate Net Thrust Produced by Turbojet?

Net Thrust Produced by Turbojet calculator uses Net Thrust of Turbojet = Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*(Exit Velocity-Flight Speed)+Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure) to calculate the Net Thrust of Turbojet, Net Thrust Produced by Turbojet is a measure of the forward force exerted by a turbojet engine, which is influenced by the mass flow rate, exhaust velocity, and pressure difference between the exit and ambient conditions, and is a critical parameter in the design and operation of aircraft and other propulsion systems. Net Thrust of Turbojet is denoted by T symbol.

How to calculate Net Thrust Produced by Turbojet using this online calculator? To use this online calculator for Net Thrust Produced by Turbojet, enter Mass Flow Rate Turbojet (m_a), Fuel Air Ratio (f), Exit Velocity (V_e), Flight Speed (V), Nozzle Exit Area (A_e), Nozzle Exit Pressure (p_e) & Ambient Pressure (p_∞) and hit the calculate button. Here is how the Net Thrust Produced by Turbojet calculation can be explained with given input values -> 56.9309 = 5*(1+0.008)*(213-130)+0.0589*(982-101).

FAQ

What is Net Thrust Produced by Turbojet?

Net Thrust Produced by Turbojet is a measure of the forward force exerted by a turbojet engine, which is influenced by the mass flow rate, exhaust velocity, and pressure difference between the exit and ambient conditions, and is a critical parameter in the design and operation of aircraft and other propulsion systems and is represented as T = m_a*(1+f)*(V_e-V)+A_e*(p_e-p_∞) or Net Thrust of Turbojet = Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*(Exit Velocity-Flight Speed)+Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure). Mass Flow Rate Turbojet represents the amount of air entering a turbojet engine per unit time, Fuel Air Ratio signifies the proportion of fuel mixed with air in a combustion system, 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, 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.

How to calculate Net Thrust Produced by Turbojet?

Net Thrust Produced by Turbojet is a measure of the forward force exerted by a turbojet engine, which is influenced by the mass flow rate, exhaust velocity, and pressure difference between the exit and ambient conditions, and is a critical parameter in the design and operation of aircraft and other propulsion systems is calculated using Net Thrust of Turbojet = Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*(Exit Velocity-Flight Speed)+Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure). To calculate Net Thrust Produced by Turbojet, you need Mass Flow Rate Turbojet (m_a), Fuel Air Ratio (f), Exit Velocity (V_e), Flight Speed (V), Nozzle Exit Area (A_e), Nozzle Exit Pressure (p_e) & Ambient Pressure (p_∞). With our tool, you need to enter the respective value for Mass Flow Rate Turbojet, Fuel Air Ratio, Exit Velocity, Flight Speed, Nozzle Exit Area, Nozzle Exit Pressure & Ambient Pressure 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 Net Thrust of Turbojet?

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

Net Thrust of Turbojet = Gross Thrust of Turbojet-Ram Drag of Turbojet

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