Mass Flow Rate of Turbojet given Gross Thrust Calculator

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

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

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Mass Flow Rate of Turbojet given Gross Thrust Solution

STEP 0: Pre-Calculation Summary

Formula Used

Mass Flow Rate Turbojet = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/((1+Fuel Air Ratio)*Exit Velocity)
m_a = (T_G-(p_e-p_∞)*A_e)/((1+f)*V_e)
This formula uses 7 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.
Gross Thrust of Turbojet - (Measured in Newton) - Gross Thrust of Turbojet is the total thrust force produced by a turbojet excluding the ram drag.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Gross Thrust of Turbojet: 1124 Newton --> 1124 Newton 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
Fuel Air Ratio: 0.008 --> No Conversion Required
Exit Velocity: 213 Meter per Second --> 213 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

m_a = (T_G-(p_e-p_∞)*A_e)/((1+f)*V_e) --> (1124-(982-101)*0.0589)/((1+0.008)*213)

Evaluating ... ...

m_a = 4.99342862731947

STEP 3: Convert Result to Output's Unit

4.99342862731947 Kilogram per Second --> No Conversion Required

FINAL ANSWER

4.99342862731947 ≈ 4.993429 Kilogram per Second <-- Mass Flow Rate Turbojet

(Calculation completed in 00.020 seconds)

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Created by Himanshu Sharma

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

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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 of Turbojet given Gross Thrust Formula

LaTeX Go

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

What is mass flow rate?

The mass flow rate is the mass of a liquid substance passing per unit time. In other words, the mass flow rate is defined as the rate of movement of liquid pass through a unit area. The mass flow is directly dependent on the density, velocity of the liquid, and area of cross-section.

How to Calculate Mass Flow Rate of Turbojet given Gross Thrust?

Mass Flow Rate of Turbojet given Gross Thrust calculator uses Mass Flow Rate Turbojet = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/((1+Fuel Air Ratio)*Exit Velocity) to calculate the Mass Flow Rate Turbojet, Mass Flow Rate of Turbojet given Gross Thrust is a measure of the rate at which mass flows through a turbojet engine, which is crucial in assessing the engine's performance and efficiency. Mass Flow Rate Turbojet is denoted by m_a symbol.

How to calculate Mass Flow Rate of Turbojet given Gross Thrust using this online calculator? To use this online calculator for Mass Flow Rate of Turbojet given Gross Thrust, enter Gross Thrust of Turbojet (T_G), Nozzle Exit Pressure (p_e), Ambient Pressure (p_∞), Nozzle Exit Area (A_e), Fuel Air Ratio (f) & Exit Velocity (V_e) and hit the calculate button. Here is how the Mass Flow Rate of Turbojet given Gross Thrust calculation can be explained with given input values -> 4.993429 = (1124-(982-101)*0.0589)/((1+0.008)*213).

FAQ

What is Mass Flow Rate of Turbojet given Gross Thrust?

Mass Flow Rate of Turbojet given Gross Thrust is a measure of the rate at which mass flows through a turbojet engine, which is crucial in assessing the engine's performance and efficiency and is represented as m_a = (T_G-(p_e-p_∞)*A_e)/((1+f)*V_e) or Mass Flow Rate Turbojet = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/((1+Fuel Air Ratio)*Exit Velocity). Gross Thrust of Turbojet is the total thrust force produced by a turbojet excluding the ram drag, 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, 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.

How to calculate Mass Flow Rate of Turbojet given Gross Thrust?

Mass Flow Rate of Turbojet given Gross Thrust is a measure of the rate at which mass flows through a turbojet engine, which is crucial in assessing the engine's performance and efficiency is calculated using Mass Flow Rate Turbojet = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/((1+Fuel Air Ratio)*Exit Velocity). To calculate Mass Flow Rate of Turbojet given Gross Thrust, you need Gross Thrust of Turbojet (T_G), Nozzle Exit Pressure (p_e), Ambient Pressure (p_∞), Nozzle Exit Area (A_e), Fuel Air Ratio (f) & Exit Velocity (V_e). With our tool, you need to enter the respective value for Gross Thrust of Turbojet, Nozzle Exit Pressure, Ambient Pressure, Nozzle Exit Area, Fuel Air Ratio & Exit Velocity 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 Gross Thrust of Turbojet, Nozzle Exit Pressure, Ambient Pressure, Nozzle Exit Area, Fuel Air Ratio & Exit Velocity. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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