Mass Flow Rate of Exhaust Gases Solution

STEP 0: Pre-Calculation Summary
Formula Used
Mass Flow Rate Turbojet = Mass Flow Rate Turbojet+Fuel Flow Rate
ma = ma+mf
This formula uses 3 Variables
Variables Used
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.
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 Flow Rate - (Measured in Kilogram per Second) - Fuel Flow Rate represents the rate at which fuel is consumed or supplied over a specified period, crucial for monitoring fuel consumption and efficiency in various engines or systems.
STEP 1: Convert Input(s) to Base Unit
Mass Flow Rate Turbojet: 5 Kilogram per Second --> 5 Kilogram per Second No Conversion Required
Fuel Flow Rate: 0.033 Kilogram per Second --> 0.033 Kilogram per Second No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
ma = ma+mf --> 5+0.033
Evaluating ... ...
ma = 5.033
STEP 3: Convert Result to Output's Unit
5.033 Kilogram per Second --> No Conversion Required
FINAL ANSWER
5.033 Kilogram per Second <-- Mass Flow Rate Turbojet
(Calculation completed in 00.004 seconds)

Credits

Created by Chilvera Bhanu Teja
Institute of Aeronautical Engineering (IARE), Hyderabad
Chilvera Bhanu Teja has created this Calculator and 300+ more calculators!
Verified by Sagar S Kulkarni
Dayananda Sagar College of Engineering (DSCE), Bengaluru
Sagar S Kulkarni has verified this Calculator and 200+ 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)

Mass Flow Rate of Exhaust Gases Formula

Mass Flow Rate Turbojet = Mass Flow Rate Turbojet+Fuel Flow Rate
ma = ma+mf

What is mass flow rate?

Mass flow rate is the mass of a fluid passing per unit time. It is also defined as the rate of movement of fluid through a unit area.

How to Calculate Mass Flow Rate of Exhaust Gases?

Mass Flow Rate of Exhaust Gases calculator uses Mass Flow Rate Turbojet = Mass Flow Rate Turbojet+Fuel Flow Rate to calculate the Mass Flow Rate Turbojet, The Mass flow rate of exhaust gases formula is defined as the sum of mass flow rate of air and mass flow rate of fuel. Mass Flow Rate Turbojet is denoted by ma symbol.

How to calculate Mass Flow Rate of Exhaust Gases using this online calculator? To use this online calculator for Mass Flow Rate of Exhaust Gases, enter Fuel Flow Rate (mf) and hit the calculate button. Here is how the Mass Flow Rate of Exhaust Gases calculation can be explained with given input values -> 6.2 = 5+0.033.

FAQ

What is Mass Flow Rate of Exhaust Gases?
The Mass flow rate of exhaust gases formula is defined as the sum of mass flow rate of air and mass flow rate of fuel and is represented as ma = ma+mf or Mass Flow Rate Turbojet = Mass Flow Rate Turbojet+Fuel Flow Rate. Fuel Flow Rate represents the rate at which fuel is consumed or supplied over a specified period, crucial for monitoring fuel consumption and efficiency in various engines or systems.
How to calculate Mass Flow Rate of Exhaust Gases?
The Mass flow rate of exhaust gases formula is defined as the sum of mass flow rate of air and mass flow rate of fuel is calculated using Mass Flow Rate Turbojet = Mass Flow Rate Turbojet+Fuel Flow Rate. To calculate Mass Flow Rate of Exhaust Gases, you need Fuel Flow Rate (mf). With our tool, you need to enter the respective value for Fuel Flow Rate 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 Mass Flow Rate Turbojet?
In this formula, Mass Flow Rate Turbojet uses Fuel Flow Rate. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Mass Flow Rate Turbojet = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/((1+Fuel Air Ratio)*Exit Velocity)
  • Mass Flow Rate Turbojet = (Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/((Exit Velocity-Flight Speed)*(1+Fuel Air Ratio))
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