Exhaust Velocity given Gross Thrust in Turbojet 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%
✖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.ⓘ Exhaust Velocity given Gross Thrust in Turbojet [V_e]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Turbojets Formulas PDF PDF Image

Exhaust Velocity given Gross Thrust in Turbojet Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

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
Mass Flow Rate Turbojet: 5 Kilogram per Second --> 5 Kilogram per Second No Conversion Required
Fuel Air Ratio: 0.008 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V_e = (T_G-(p_e-p_∞)*A_e)/(m_a*(1+f)) --> (1124-(982-101)*0.0589)/(5*(1+0.008))

Evaluating ... ...

V_e = 212.72005952381

STEP 3: Convert Result to Output's Unit

212.72005952381 Meter per Second --> No Conversion Required

FINAL ANSWER

212.72005952381 ≈ 212.7201 Meter per Second <-- Exit Velocity

(Calculation completed in 00.020 seconds)

You are here -

Home » Physics » Propulsion » Jet Propulsion » Aerospace » Turbojets » Exhaust Velocity given Gross Thrust in Turbojet

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!

< 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 Gross Thrust in Turbojet Formula

LaTeX Go

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

What is the 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 Gross Thrust in Turbojet?

Exhaust Velocity given Gross Thrust in Turbojet calculator uses Exit Velocity = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/(Mass Flow Rate Turbojet*(1+Fuel Air Ratio)) to calculate the Exit Velocity, Exhaust Velocity given Gross Thrust in Turbojet is a measure of the velocity at which gases escape the nozzle of a turbojet engine, affecting the engine's performance and efficiency, and is influenced by factors such as gross thrust, atmospheric pressure, and nozzle area. Exit Velocity is denoted by V_e symbol.

How to calculate Exhaust Velocity given Gross Thrust in Turbojet using this online calculator? To use this online calculator for Exhaust Velocity given Gross Thrust in Turbojet, enter Gross Thrust of Turbojet (T_G), Nozzle Exit Pressure (p_e), Ambient Pressure (p_∞), Nozzle Exit Area (A_e), Mass Flow Rate Turbojet (m_a) & Fuel Air Ratio (f) and hit the calculate button. Here is how the Exhaust Velocity given Gross Thrust in Turbojet calculation can be explained with given input values -> 213.355 = (1124-(982-101)*0.0589)/(5*(1+0.008)).

FAQ

What is Exhaust Velocity given Gross Thrust in Turbojet?

Exhaust Velocity given Gross Thrust in Turbojet is a measure of the velocity at which gases escape the nozzle of a turbojet engine, affecting the engine's performance and efficiency, and is influenced by factors such as gross thrust, atmospheric pressure, and nozzle area and is represented as V_e = (T_G-(p_e-p_∞)*A_e)/(m_a*(1+f)) or Exit Velocity = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/(Mass Flow Rate Turbojet*(1+Fuel Air Ratio)). 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, 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.

How to calculate Exhaust Velocity given Gross Thrust in Turbojet?

Exhaust Velocity given Gross Thrust in Turbojet is a measure of the velocity at which gases escape the nozzle of a turbojet engine, affecting the engine's performance and efficiency, and is influenced by factors such as gross thrust, atmospheric pressure, and nozzle area is calculated using Exit Velocity = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/(Mass Flow Rate Turbojet*(1+Fuel Air Ratio)). To calculate Exhaust Velocity given Gross Thrust in Turbojet, you need Gross Thrust of Turbojet (T_G), Nozzle Exit Pressure (p_e), Ambient Pressure (p_∞), Nozzle Exit Area (A_e), Mass Flow Rate Turbojet (m_a) & Fuel Air Ratio (f). With our tool, you need to enter the respective value for Gross Thrust of Turbojet, Nozzle Exit Pressure, Ambient Pressure, Nozzle Exit Area, Mass Flow Rate Turbojet & Fuel Air Ratio 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 Gross Thrust of Turbojet, Nozzle Exit Pressure, Ambient Pressure, Nozzle Exit Area, Mass Flow Rate Turbojet & Fuel Air Ratio. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

Home

FREE PDFs

🔍 Search