Nozzle Exit Area in Turbojet 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%
✖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 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 in Turbojet [A_e]

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Nozzle Exit Area in Turbojet Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

Nozzle Exit Area - (Measured in Square Meter) - Nozzle Exit Area refers to the cross-sectional area at the exit of a nozzle.
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 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

Net Thrust of Turbojet: 469 Newton --> 469 Newton No Conversion Required
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 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

A_e = (T-m_a*(1+f)*(V_e-V))/(p_e-p_∞) --> (469-5*(1+0.008)*(213-130))/(982-101)

Evaluating ... ...

A_e = 0.0575255391600454

STEP 3: Convert Result to Output's Unit

0.0575255391600454 Square Meter --> No Conversion Required

FINAL ANSWER

0.0575255391600454 ≈ 0.057526 Square Meter <-- Nozzle Exit Area

(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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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

Nozzle Exit Area in Turbojet Formula

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)
A_e = (T-m_a*(1+f)*(V_e-V))/(p_e-p_∞)

What is nozzle of jet?

The nozzle sits downstream of the power turbine. A nozzle is a relatively simple device, just a specially shaped tube through which hot gases flow.

How to Calculate Nozzle Exit Area in Turbojet?

Nozzle Exit Area in Turbojet calculator uses Nozzle Exit Area = (Net Thrust of Turbojet-Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*(Exit Velocity-Flight Speed))/(Nozzle Exit Pressure-Ambient Pressure) to calculate the Nozzle Exit Area, The Nozzle Exit Area in Turbojet is a measure of the cross-sectional area at the exit plane of a turbojet engine nozzle, which plays a critical role in determining the engine's performance and efficiency by controlling the exhaust velocity of gases. Nozzle Exit Area is denoted by A_e symbol.

How to calculate Nozzle Exit Area in Turbojet using this online calculator? To use this online calculator for Nozzle Exit Area in Turbojet, enter Net Thrust of Turbojet (T), Mass Flow Rate Turbojet (m_a), Fuel Air Ratio (f), Exit Velocity (V_e), Flight Speed (V), Nozzle Exit Pressure (p_e) & Ambient Pressure (p_∞) and hit the calculate button. Here is how the Nozzle Exit Area in Turbojet calculation can be explained with given input values -> 0.526629 = (469-5*(1+0.008)*(213-130))/(982-101).

FAQ

What is Nozzle Exit Area in Turbojet?

The Nozzle Exit Area in Turbojet is a measure of the cross-sectional area at the exit plane of a turbojet engine nozzle, which plays a critical role in determining the engine's performance and efficiency by controlling the exhaust velocity of gases and is represented as A_e = (T-m_a*(1+f)*(V_e-V))/(p_e-p_∞) or 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 of Turbojet denotes the total thrust or forward force exerted by the engine to propel an aircraft forward, 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 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 Nozzle Exit Area in Turbojet?

The Nozzle Exit Area in Turbojet is a measure of the cross-sectional area at the exit plane of a turbojet engine nozzle, which plays a critical role in determining the engine's performance and efficiency by controlling the exhaust velocity of gases is calculated using Nozzle Exit Area = (Net Thrust of Turbojet-Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*(Exit Velocity-Flight Speed))/(Nozzle Exit Pressure-Ambient Pressure). To calculate Nozzle Exit Area in Turbojet, you need Net Thrust of Turbojet (T), Mass Flow Rate Turbojet (m_a), Fuel Air Ratio (f), Exit Velocity (V_e), Flight Speed (V), Nozzle Exit Pressure (p_e) & Ambient Pressure (p_∞). With our tool, you need to enter the respective value for Net Thrust of Turbojet, Mass Flow Rate Turbojet, Fuel Air Ratio, Exit Velocity, Flight Speed, 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.

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