Exhaust Velocity given Thrust 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%
✖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 refers to the pressure of the surrounding environment, typically measured relative to a vacuum.ⓘ Ambient Pressure [p_∞]			+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%
✖Flight Speed refers to the velocity at which an aircraft travel through the air.ⓘ Flight Speed [V]			+10% -10%

✖Exit Velocity refers to the speed at which gases expand at the exit of nozzle of a turbojet engine.ⓘ Exhaust Velocity given Thrust in Turbojet [V_e]

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Exhaust Velocity given Thrust in Turbojet Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.
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 refers to the pressure of the surrounding environment, typically measured relative to a vacuum.
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.
Flight Speed - (Measured in Meter per Second) - Flight Speed refers to the velocity at which an aircraft travel through the air.

STEP 1: Convert Input(s) to Base Unit

Net Thrust of Turbojet: 469 Newton --> 469 Newton 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
Mass Flow Rate Turbojet: 5 Kilogram per Second --> 5 Kilogram per Second No Conversion Required
Fuel Air Ratio: 0.008 --> No Conversion Required
Flight Speed: 130 Meter per Second --> 130 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V_e = (T-A_e*(p_e-p_∞))/(m_a*(1+f))+V --> (469-0.0589*(982-101))/(5*(1+0.008))+130

Evaluating ... ...

V_e = 212.759742063492

STEP 3: Convert Result to Output's Unit

212.759742063492 Meter per Second --> No Conversion Required

FINAL ANSWER

212.759742063492 ≈ 212.7597 Meter per Second <-- Exit Velocity

(Calculation completed in 00.008 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!

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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

Exhaust Velocity given Thrust in Turbojet Formula

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

What is expansion velocity?

Velocity is the directional speed of an object in motion as an indication of its rate of change in position as observed from a particular frame of reference and as measured by a particular standard of time.

How to Calculate Exhaust Velocity given Thrust in Turbojet?

Exhaust Velocity given Thrust in Turbojet calculator uses Exit Velocity = (Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/(Mass Flow Rate Turbojet*(1+Fuel Air Ratio))+Flight Speed to calculate the Exit Velocity, Exhaust Velocity given Thrust in Turbojet is a measure of the speed at which gases exit the back of a turbojet engine, which is crucial in determining the engine's efficiency and overall performance. It is an important parameter in aerospace engineering, as it affects the thrust-to-weight ratio and overall propulsion of an aircraft. Exit Velocity is denoted by V_e symbol.

How to calculate Exhaust Velocity given Thrust in Turbojet using this online calculator? To use this online calculator for Exhaust Velocity given Thrust in Turbojet, enter Net Thrust of Turbojet (T), Nozzle Exit Area (A_e), Nozzle Exit Pressure (p_e), Ambient Pressure (p_∞), Mass Flow Rate Turbojet (m_a), Fuel Air Ratio (f) & Flight Speed (V) and hit the calculate button. Here is how the Exhaust Velocity given Thrust in Turbojet calculation can be explained with given input values -> 294.7597 = (469-0.0589*(982-101))/(5*(1+0.008))+130.

FAQ

What is Exhaust Velocity given Thrust in Turbojet?

Exhaust Velocity given Thrust in Turbojet is a measure of the speed at which gases exit the back of a turbojet engine, which is crucial in determining the engine's efficiency and overall performance. It is an important parameter in aerospace engineering, as it affects the thrust-to-weight ratio and overall propulsion of an aircraft and is represented as V_e = (T-A_e*(p_e-p_∞))/(m_a*(1+f))+V or Exit Velocity = (Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/(Mass Flow Rate Turbojet*(1+Fuel Air Ratio))+Flight Speed. Net Thrust of Turbojet denotes the total thrust or forward force exerted by the engine to propel an aircraft forward, 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 refers to the pressure of the surrounding environment, typically measured relative to a vacuum, 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 & Flight Speed refers to the velocity at which an aircraft travel through the air.

How to calculate Exhaust Velocity given Thrust in Turbojet?

Exhaust Velocity given Thrust in Turbojet is a measure of the speed at which gases exit the back of a turbojet engine, which is crucial in determining the engine's efficiency and overall performance. It is an important parameter in aerospace engineering, as it affects the thrust-to-weight ratio and overall propulsion of an aircraft is calculated using Exit Velocity = (Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/(Mass Flow Rate Turbojet*(1+Fuel Air Ratio))+Flight Speed. To calculate Exhaust Velocity given Thrust in Turbojet, you need Net Thrust of Turbojet (T), Nozzle Exit Area (A_e), Nozzle Exit Pressure (p_e), Ambient Pressure (p_∞), Mass Flow Rate Turbojet (m_a), Fuel Air Ratio (f) & Flight Speed (V). With our tool, you need to enter the respective value for Net Thrust of Turbojet, Nozzle Exit Area, Nozzle Exit Pressure, Ambient Pressure, Mass Flow Rate Turbojet, Fuel Air Ratio & Flight Speed 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 Exit Velocity?

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

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

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