Nozzle Exit Area in 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

✖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 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%

✖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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Formula

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Nozzle Exit Area in Turbojet

Formula

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

Example

`"0.057526m²"=("469N"-"5kg/s"*(1+"0.008")*("213m/s"-"130m/s"))/("982Pa"-"101Pa")`

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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 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

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 00.004 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)

Nozzle Exit Area in Turbojet Formula

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, Nozzle Exit Area in Turbojet formula is defined as the cross-sectional area at the exit of a nozzle of a turbojet engine, which is used to produce thrust. 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?

Nozzle Exit Area in Turbojet formula is defined as the cross-sectional area at the exit of a nozzle of a turbojet engine, which is used to produce thrust 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 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 Nozzle Exit Area in Turbojet?

Nozzle Exit Area in Turbojet formula is defined as the cross-sectional area at the exit of a nozzle of a turbojet engine, which is used to produce thrust 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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