Turbofan thrust Calculator

✖Mass Flow Rate Core refers to the rate at which air flows through the core of a turbofan engine, specifically through the combustion chamber and the turbine.ⓘ Mass Flow Rate Core [m_c]			+10% -10%
✖Exit Velocity Core Nozzle is the speed at which exhaust gases exit the primary nozzle of a turbofan engine.ⓘ Exit Velocity Core Nozzle [V_j,c]			+10% -10%
✖Flight Speed refers to the velocity at which an aircraft travels through the air.ⓘ Flight Speed [V]			+10% -10%
✖Mass Flow Rate Bypass refers to the rate at which air bypasses the core of a turbofan engine and flows through the bypass duct.ⓘ Mass Flow Rate Bypass [ṁ_b]			+10% -10%
✖Exit Velocity Bypass Nozzle is the speed at which exhaust gases exit the secondary nozzle of a turbofan exit.ⓘ Exit Velocity Bypass Nozzle [V_j,b]			+10% -10%

✖Turbofan Thrust is the total thrust produced by jet core efflux and bypass air which has been accelerated by a ducted fan.ⓘ Turbofan thrust [T]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Turbofans Formulas PDF PDF Image

Turbofan thrust Solution

STEP 0: Pre-Calculation Summary

Formula Used

Turbofan Thrust = Mass Flow Rate Core*(Exit Velocity Core Nozzle-Flight Speed)+Mass Flow Rate Bypass*(Exit Velocity Bypass Nozzle-Flight Speed)
T = m_c*(V_j,c-V)+ṁ_b*(V_j,b-V)
This formula uses 6 Variables

Variables Used

Turbofan Thrust - (Measured in Newton) - Turbofan Thrust is the total thrust produced by jet core efflux and bypass air which has been accelerated by a ducted fan.
Mass Flow Rate Core - (Measured in Kilogram per Second) - Mass Flow Rate Core refers to the rate at which air flows through the core of a turbofan engine, specifically through the combustion chamber and the turbine.
Exit Velocity Core Nozzle - (Measured in Meter per Second) - Exit Velocity Core Nozzle is the speed at which exhaust gases exit the primary nozzle of a turbofan engine.
Flight Speed - (Measured in Meter per Second) - Flight Speed refers to the velocity at which an aircraft travels through the air.
Mass Flow Rate Bypass - (Measured in Kilogram per Second) - Mass Flow Rate Bypass refers to the rate at which air bypasses the core of a turbofan engine and flows through the bypass duct.
Exit Velocity Bypass Nozzle - (Measured in Meter per Second) - Exit Velocity Bypass Nozzle is the speed at which exhaust gases exit the secondary nozzle of a turbofan exit.

STEP 1: Convert Input(s) to Base Unit

Mass Flow Rate Core: 43 Kilogram per Second --> 43 Kilogram per Second No Conversion Required
Exit Velocity Core Nozzle: 300 Meter per Second --> 300 Meter per Second No Conversion Required
Flight Speed: 198 Meter per Second --> 198 Meter per Second No Conversion Required
Mass Flow Rate Bypass: 258 Kilogram per Second --> 258 Kilogram per Second No Conversion Required
Exit Velocity Bypass Nozzle: 250 Meter per Second --> 250 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

T = m_c*(V_j,c-V)+ṁ_b*(V_j,b-V) --> 43*(300-198)+258*(250-198)

Evaluating ... ...

T = 17802

STEP 3: Convert Result to Output's Unit

17802 Newton -->17.802 Kilonewton (Check conversion here)

FINAL ANSWER

17.802 Kilonewton <-- Turbofan Thrust

(Calculation completed in 00.020 seconds)

You are here -

Home » Physics » Propulsion » Jet Propulsion » Aerospace » Turbofans » Turbofan thrust

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!

< Turbofans Calculators

Turbofan thrust

LaTeX Go Turbofan Thrust = Mass Flow Rate Core*(Exit Velocity Core Nozzle-Flight Speed)+Mass Flow Rate Bypass*(Exit Velocity Bypass Nozzle-Flight Speed)

Cooling Effectiveness

LaTeX Go Cooling Effectiveness = (Temperature of Hot Gas Stream-Temperature of Metal)/(Temperature of Hot Gas Stream-Temperature of Cooling Air)

Total mass flow rate through turbofan engine

LaTeX Go Mass Flow Rate = Mass Flow Rate Core+Mass Flow Rate Bypass

Bypass Ratio

LaTeX Go Bypass Ratio = Mass Flow Rate Bypass/Mass Flow Rate Core

Turbofan thrust Formula

LaTeX Go

Turbofan Thrust = Mass Flow Rate Core*(Exit Velocity Core Nozzle-Flight Speed)+Mass Flow Rate Bypass*(Exit Velocity Bypass Nozzle-Flight Speed)
T = m_c*(V_j,c-V)+ṁ_b*(V_j,b-V)

What is turbofan thrust?

A turbofan thrust is thrust using a combination of jet core efflux and bypass air which has been accelerated by a ducted fan that is driven by the jet core.

How to Calculate Turbofan thrust?

Turbofan thrust calculator uses Turbofan Thrust = Mass Flow Rate Core*(Exit Velocity Core Nozzle-Flight Speed)+Mass Flow Rate Bypass*(Exit Velocity Bypass Nozzle-Flight Speed) to calculate the Turbofan Thrust, Turbofan thrust is a measure of the forward force generated by a turbofan engine, which is influenced by the mass flow rate and velocity of the hot gases expelled out of the nozzle and the bypass flow. It is a critical parameter in aerospace engineering, used to evaluate the performance of a turbofan engine. Turbofan Thrust is denoted by T symbol.

How to calculate Turbofan thrust using this online calculator? To use this online calculator for Turbofan thrust, enter Mass Flow Rate Core (m_c), Exit Velocity Core Nozzle (V_j,c), Flight Speed (V), Mass Flow Rate Bypass (ṁ_b) & Exit Velocity Bypass Nozzle (V_j,b) and hit the calculate button. Here is how the Turbofan thrust calculation can be explained with given input values -> 0.017802 = 43*(300-198)+258*(250-198).

FAQ

What is Turbofan thrust?

Turbofan thrust is a measure of the forward force generated by a turbofan engine, which is influenced by the mass flow rate and velocity of the hot gases expelled out of the nozzle and the bypass flow. It is a critical parameter in aerospace engineering, used to evaluate the performance of a turbofan engine and is represented as T = m_c*(V_j,c-V)+ṁ_b*(V_j,b-V) or Turbofan Thrust = Mass Flow Rate Core*(Exit Velocity Core Nozzle-Flight Speed)+Mass Flow Rate Bypass*(Exit Velocity Bypass Nozzle-Flight Speed). Mass Flow Rate Core refers to the rate at which air flows through the core of a turbofan engine, specifically through the combustion chamber and the turbine, Exit Velocity Core Nozzle is the speed at which exhaust gases exit the primary nozzle of a turbofan engine, Flight Speed refers to the velocity at which an aircraft travels through the air, Mass Flow Rate Bypass refers to the rate at which air bypasses the core of a turbofan engine and flows through the bypass duct & Exit Velocity Bypass Nozzle is the speed at which exhaust gases exit the secondary nozzle of a turbofan exit.

How to calculate Turbofan thrust?

Turbofan thrust is a measure of the forward force generated by a turbofan engine, which is influenced by the mass flow rate and velocity of the hot gases expelled out of the nozzle and the bypass flow. It is a critical parameter in aerospace engineering, used to evaluate the performance of a turbofan engine is calculated using Turbofan Thrust = Mass Flow Rate Core*(Exit Velocity Core Nozzle-Flight Speed)+Mass Flow Rate Bypass*(Exit Velocity Bypass Nozzle-Flight Speed). To calculate Turbofan thrust, you need Mass Flow Rate Core (m_c), Exit Velocity Core Nozzle (V_j,c), Flight Speed (V), Mass Flow Rate Bypass (ṁ_b) & Exit Velocity Bypass Nozzle (V_j,b). With our tool, you need to enter the respective value for Mass Flow Rate Core, Exit Velocity Core Nozzle, Flight Speed, Mass Flow Rate Bypass & Exit Velocity Bypass Nozzle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

Home

FREE PDFs

🔍 Search