Momentum Thrust Calculator

✖Mass Flow Rate represents the amount of mass passing through a system per unit of time.ⓘ Mass Flow Rate [m_a]			+10% -10%
✖Fuel Air Ratio is the ratio of mass flow rate of fuel to the mass flow rate of air.ⓘ Fuel Air Ratio [f]			+10% -10%
✖Exit Velocity refers to the speed at which gases expand at the exit of nozzle of a engine.ⓘ Exit Velocity [V_e]			+10% -10%
✖Flight Speed refers to the velocity at which an aircraft moves through the air.ⓘ Flight Speed [V]			+10% -10%

✖Ideal Thrust is the thrust produced by an engine when nozzle exit pressure is same as ambient pressure or nozzle is perfectly expanded.ⓘ Momentum Thrust [T_ideal]

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Momentum Thrust Solution

STEP 0: Pre-Calculation Summary

Formula Used

Ideal Thrust = Mass Flow Rate*((1+Fuel Air Ratio)*Exit Velocity-Flight Speed)
T_ideal = m_a*((1+f)*V_e-V)
This formula uses 5 Variables

Variables Used

Ideal Thrust - (Measured in Newton) - Ideal Thrust is the thrust produced by an engine when nozzle exit pressure is same as ambient pressure or nozzle is perfectly expanded.
Mass Flow Rate - (Measured in Kilogram per Second) - Mass Flow Rate represents the amount of mass passing through a system per unit of time.
Fuel Air Ratio - Fuel Air Ratio is the ratio of mass flow rate of fuel to the mass flow rate of air.
Exit Velocity - (Measured in Meter per Second) - Exit Velocity refers to the speed at which gases expand at the exit of nozzle of a engine.
Flight Speed - (Measured in Meter per Second) - Flight Speed refers to the velocity at which an aircraft moves through the air.

STEP 1: Convert Input(s) to Base Unit

Mass Flow Rate: 3.5 Kilogram per Second --> 3.5 Kilogram per Second No Conversion Required
Fuel Air Ratio: 0.009 --> No Conversion Required
Exit Velocity: 248 Meter per Second --> 248 Meter per Second No Conversion Required
Flight Speed: 111 Meter per Second --> 111 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

T_ideal = m_a*((1+f)*V_e-V) --> 3.5*((1+0.009)*248-111)

Evaluating ... ...

T_ideal = 487.312

STEP 3: Convert Result to Output's Unit

487.312 Newton --> No Conversion Required

FINAL ANSWER

487.312 Newton <-- Ideal Thrust

(Calculation completed in 00.004 seconds)

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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!

< Thrust Generation Calculators

Total Thrust given Efficiency and Enthalpy

LaTeX Go Total Thrust = Mass Flow Rate*((sqrt(2*Enthalpy Drop in Nozzle*Nozzle Efficiency))-Flight Speed+(sqrt(Turbine Efficiency*Efficiency of Transmission*Enthalpy Drop in Turbine)))

Thrust power

LaTeX Go Thrust Power = Mass Flow Rate*Flight Speed*(Exit Velocity-Flight Speed)

Ideal Thrust given Effective Speed Ratio

LaTeX Go Ideal Thrust = Mass Flow Rate*Flight Speed*((1/Effective Speed Ratio)-1)

Specific thrust

LaTeX Go Specific Thrust = Exit Velocity-Flight Speed

Momentum Thrust Formula

LaTeX Go

Ideal Thrust = Mass Flow Rate*((1+Fuel Air Ratio)*Exit Velocity-Flight Speed)
T_ideal = m_a*((1+f)*V_e-V)

What is thrust?

Thrust is the force which moves an aircraft through the air. Thrust is used to overcome the drag of an airplane, and to overcome the weight of a rocket.

How to Calculate Momentum Thrust?

Momentum Thrust calculator uses Ideal Thrust = Mass Flow Rate*((1+Fuel Air Ratio)*Exit Velocity-Flight Speed) to calculate the Ideal Thrust, Momentum Thrust is a measure of the forward force produced by an aircraft or spacecraft, calculated by considering the mass flow rate, fuel-air ratio, exit velocity, and flight speed, providing a crucial parameter in aerospace engineering to evaluate the performance and efficiency of propulsion systems. Ideal Thrust is denoted by T_ideal symbol.

How to calculate Momentum Thrust using this online calculator? To use this online calculator for Momentum Thrust, enter Mass Flow Rate (m_a), Fuel Air Ratio (f), Exit Velocity (V_e) & Flight Speed (V) and hit the calculate button. Here is how the Momentum Thrust calculation can be explained with given input values -> 487.312 = 3.5*((1+0.009)*248-111).

FAQ

What is Momentum Thrust?

Momentum Thrust is a measure of the forward force produced by an aircraft or spacecraft, calculated by considering the mass flow rate, fuel-air ratio, exit velocity, and flight speed, providing a crucial parameter in aerospace engineering to evaluate the performance and efficiency of propulsion systems and is represented as T_ideal = m_a*((1+f)*V_e-V) or Ideal Thrust = Mass Flow Rate*((1+Fuel Air Ratio)*Exit Velocity-Flight Speed). Mass Flow Rate represents the amount of mass passing through a system per unit of time, Fuel Air Ratio is the ratio of mass flow rate of fuel to the mass flow rate of air, Exit Velocity refers to the speed at which gases expand at the exit of nozzle of a engine & Flight Speed refers to the velocity at which an aircraft moves through the air.

How to calculate Momentum Thrust?

Momentum Thrust is a measure of the forward force produced by an aircraft or spacecraft, calculated by considering the mass flow rate, fuel-air ratio, exit velocity, and flight speed, providing a crucial parameter in aerospace engineering to evaluate the performance and efficiency of propulsion systems is calculated using Ideal Thrust = Mass Flow Rate*((1+Fuel Air Ratio)*Exit Velocity-Flight Speed). To calculate Momentum Thrust, you need Mass Flow Rate (m_a), Fuel Air Ratio (f), Exit Velocity (V_e) & Flight Speed (V). With our tool, you need to enter the respective value for Mass Flow Rate, Fuel Air Ratio, Exit Velocity & 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 Ideal Thrust?

In this formula, Ideal Thrust uses Mass Flow Rate, Fuel Air Ratio, Exit Velocity & Flight Speed. We can use 3 other way(s) to calculate the same, which is/are as follows -

Ideal Thrust = Mass Flow Rate*Flight Speed*((1/Effective Speed Ratio)-1)
Ideal Thrust = Mass Flow Rate*(Exit Velocity-Flight Speed)
Ideal Thrust = Mass Flow Rate*(Exit Velocity-Flight Speed)

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