Net Thrust Produced by Turbojet Calculator

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Jet Propulsion

Components of Gas Turbine

Rocket Propulsion

Thermodynamics and Governing Equations

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Turbojets

Performance Parameters

Turbofans

Turbomachinery Equations

Turboprops

✖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 at the Periphery of the Storm is the pressure of the surrounding medium, such as a gas or liquid, in contact with the reference.ⓘ 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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Formula

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Net Thrust Produced by Turbojet

Formula

`"T" = "m"_{"a"}*(1+"f")*("V"_{"e"}-"V")+"A"_{"e"}*("p"_{"e"}-"p"_{"∞"})`

Example

`"470.2109N"="5kg/s"*(1+"0.008")*("213m/s"-"130m/s")+"0.0589m²"*("982Pa"-"101Pa")`

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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 at the Periphery of the Storm is the pressure of the surrounding medium, such as a gas or liquid, in contact with the reference.

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 00.004 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

Kartikay Pandit has verified this Calculator and 400+ more calculators!

< 14 Turbojets Calculators

Mass Flow Rate in Turbojet given Thrust

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))

Exhaust Velocity given Thrust in Turbojet

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

Flight Speed given Thrust in Turbojet

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

Nozzle Exit Area in Turbojet

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)

Net Thrust Produced by Turbojet

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)

Exhaust Velocity given Gross Thrust in Turbojet

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

Mass Flow Rate of Turbojet given Gross Thrust

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

Turbojet Gross Thrust

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

Thermal efficiency of turbojet engine

Go Turbojet Thermal Efficiency = Propulsive Power/(Fuel Flow Rate*Fuel Calorific Value)

Net Thrust of Turbojet given Gross Thrust

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

Gross Thrust of Turbojet given Net Thrust

Go Gross Thrust of Turbojet = Net Thrust of Turbojet+Ram Drag of Turbojet

Ram Drag of Turbojet given Gross Thrust

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

Mass Flow Rate of Exhaust Gases

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

Mass Flow Rate of Exhaust Gases given Fuel Air Ratio

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

Net Thrust Produced by Turbojet Formula

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 formula is defined as the total thrust produced by a turbojet engine considering flight speed, exhaust speed, fuel-to-air ratio and mass flow rate of air. 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 formula is defined as the total thrust produced by a turbojet engine considering flight speed, exhaust speed, fuel-to-air ratio and mass flow rate of air 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 at the Periphery of the Storm is the pressure of the surrounding medium, such as a gas or liquid, in contact with the reference.

How to calculate Net Thrust Produced by Turbojet?

Net Thrust Produced by Turbojet formula is defined as the total thrust produced by a turbojet engine considering flight speed, exhaust speed, fuel-to-air ratio and mass flow rate of air 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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