Turbojet Gross Thrust 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%
✖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%
✖Nozzle Exit Area refers to the cross-sectional area at the exit of a nozzle.ⓘ Nozzle Exit Area [A_e]			+10% -10%

✖Gross Thrust of Turbojet is the total thrust force produced by a turbojet excluding the ram drag.ⓘ Turbojet Gross Thrust [T_G]

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Turbojet Gross Thrust Solution

STEP 0: Pre-Calculation Summary

Formula Used

Gross Thrust of Turbojet = Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*Exit Velocity+(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area
T_G = m_a*(1+f)*V_e+(p_e-p_∞)*A_e
This formula uses 7 Variables

Variables Used

Gross Thrust of Turbojet - (Measured in Newton) - Gross Thrust of Turbojet is the total thrust force produced by a turbojet excluding the ram drag.
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.
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.
Nozzle Exit Area - (Measured in Square Meter) - Nozzle Exit Area refers to the cross-sectional area at the exit of a nozzle.

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
Nozzle Exit Pressure: 982 Pascal --> 982 Pascal No Conversion Required
Ambient Pressure: 101 Pascal --> 101 Pascal No Conversion Required
Nozzle Exit Area: 0.0589 Square Meter --> 0.0589 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

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

Evaluating ... ...

T_G = 1125.4109

STEP 3: Convert Result to Output's Unit

1125.4109 Newton --> No Conversion Required

FINAL ANSWER

1125.4109 ≈ 1125.411 Newton <-- Gross Thrust of Turbojet

(Calculation completed in 00.004 seconds)

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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

Turbojet Gross Thrust Formula

LaTeX Go

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

What is turbojet thrust?

A turbojet engine is a jet engine which produces all of its thrust by ejecting a high energy gas stream from the engine exhaust nozzle, this is known as turbojet thrust.

How to Calculate Turbojet Gross Thrust?

Turbojet Gross Thrust calculator uses Gross Thrust of Turbojet = Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*Exit Velocity+(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area to calculate the Gross Thrust of Turbojet, Turbojet Gross Thrust is a measure of the total thrust produced by a turbojet engine, taking into account the mass flow rate, exhaust velocity, and pressure difference between the exhaust and ambient conditions. This calculation is essential for evaluating the performance and efficiency of turbojet engines in aircraft propulsion systems. Gross Thrust of Turbojet is denoted by T_G symbol.

How to calculate Turbojet Gross Thrust using this online calculator? To use this online calculator for Turbojet Gross Thrust, enter Mass Flow Rate Turbojet (m_a), Fuel Air Ratio (f), Exit Velocity (V_e), Nozzle Exit Pressure (p_e), Ambient Pressure (p_∞) & Nozzle Exit Area (A_e) and hit the calculate button. Here is how the Turbojet Gross Thrust calculation can be explained with given input values -> 1122.216 = 5*(1+0.008)*213+(982-101)*0.0589.

FAQ

What is Turbojet Gross Thrust?

Turbojet Gross Thrust is a measure of the total thrust produced by a turbojet engine, taking into account the mass flow rate, exhaust velocity, and pressure difference between the exhaust and ambient conditions. This calculation is essential for evaluating the performance and efficiency of turbojet engines in aircraft propulsion systems and is represented as T_G = m_a*(1+f)*V_e+(p_e-p_∞)*A_e or 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 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, 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 & Nozzle Exit Area refers to the cross-sectional area at the exit of a nozzle.

How to calculate Turbojet Gross Thrust?

Turbojet Gross Thrust is a measure of the total thrust produced by a turbojet engine, taking into account the mass flow rate, exhaust velocity, and pressure difference between the exhaust and ambient conditions. This calculation is essential for evaluating the performance and efficiency of turbojet engines in aircraft propulsion systems is calculated using Gross Thrust of Turbojet = Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*Exit Velocity+(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area. To calculate Turbojet Gross Thrust, you need Mass Flow Rate Turbojet (m_a), Fuel Air Ratio (f), Exit Velocity (V_e), Nozzle Exit Pressure (p_e), Ambient Pressure (p_∞) & Nozzle Exit Area (A_e). With our tool, you need to enter the respective value for Mass Flow Rate Turbojet, Fuel Air Ratio, Exit Velocity, Nozzle Exit Pressure, Ambient Pressure & Nozzle Exit Area 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 Gross Thrust of Turbojet?

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

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

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