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Exhaust Velocity given Gross Thrust in Turbojet Calculator

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✖Gross Thrust of Turbojet is the total thrust force produced by a turbojet excluding the ram drag.ⓘ Gross Thrust of Turbojet [TG]
+10%
-10%
✖Nozzle Exit Pressure refers to the pressure at the exit of a nozzle or exhaust of a system.ⓘ Nozzle Exit Pressure [pe]
+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 [Ae]
+10%
-10%
✖Mass Flow Rate Turbojet represents the amount of air entering a turbojet engine per unit time.ⓘ Mass Flow Rate Turbojet [ma]
+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 [Ve]
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Exhaust Velocity given Gross Thrust in Turbojet

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

Example
`"212.7201m/s"=("1124N"-("982Pa"-"101Pa")*"0.0589m²")/("5kg/s"*(1+"0.008"))`

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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))
Ve = (TG-(pe-p∞)*Ae)/(ma*(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 at the Periphery of the Storm is the pressure of the surrounding medium, such as a gas or liquid, in contact with the reference.
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
Ve = (TG-(pe-p∞)*Ae)/(ma*(1+f)) --> (1124-(982-101)*0.0589)/(5*(1+0.008))
Evaluating ... ...
Ve = 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 00.004 seconds)
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Home » Physics » Aeroengines » Jet Propulsion » 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!

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)

Exhaust Velocity given Gross Thrust in Turbojet Formula

Exit Velocity = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/(Mass Flow Rate Turbojet*(1+Fuel Air Ratio))
Ve = (TG-(pe-p∞)*Ae)/(ma*(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 defined as the velocity of exhaust gases exiting from the nozzle of a turbojet engine. Exit Velocity is denoted by Ve 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 (TG), Nozzle Exit Pressure (pe), Ambient Pressure (p∞), Nozzle Exit Area (Ae), Mass Flow Rate Turbojet (ma) & 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 defined as the velocity of exhaust gases exiting from the nozzle of a turbojet engine and is represented as Ve = (TG-(pe-p∞)*Ae)/(ma*(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 at the Periphery of the Storm is the pressure of the surrounding medium, such as a gas or liquid, in contact with the reference, 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 defined as the velocity of exhaust gases exiting from the nozzle of a turbojet engine 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 (TG), Nozzle Exit Pressure (pe), Ambient Pressure (p∞), Nozzle Exit Area (Ae), Mass Flow Rate Turbojet (ma) & 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
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