Mass Flow Rate given Ideal Thrust Calculator

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

✖Mass Flow Rate represents the amount of mass passing through a system per unit of time.ⓘ Mass Flow Rate given Ideal Thrust [m_a]

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Mass Flow Rate given Ideal Thrust Solution

STEP 0: Pre-Calculation Summary

Formula Used

Mass Flow Rate = Ideal Thrust/(Exit Velocity-Flight Speed)
m_a = T_ideal/(V_e-V)
This formula uses 4 Variables

Variables Used

Mass Flow Rate - (Measured in Kilogram per Second) - Mass Flow Rate represents the amount of mass passing through a system per unit of time.
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.
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

Ideal Thrust: 479.5 Newton --> 479.5 Newton 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

m_a = T_ideal/(V_e-V) --> 479.5/(248-111)

Evaluating ... ...

m_a = 3.5

STEP 3: Convert Result to Output's Unit

3.5 Kilogram per Second --> No Conversion Required

FINAL ANSWER

3.5 Kilogram per Second <-- Mass Flow Rate

(Calculation completed in 00.004 seconds)

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Created by Himanshu Sharma

National Institute of Technology, Hamirpur (NITH), Himachal Pradesh

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< 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

Mass Flow Rate given Ideal Thrust Formula

LaTeX Go

Mass Flow Rate = Ideal Thrust/(Exit Velocity-Flight Speed)
m_a = T_ideal/(V_e-V)

What is mass flow rate?'

The mass flow rate is the mass of a liquid substance passing per unit time. In other words, the mass flow rate is defined as the rate of movement of liquid pass through a unit area. The mass flow is directly dependent on the density, velocity of the liquid, and area of cross-section.

How to Calculate Mass Flow Rate given Ideal Thrust?

Mass Flow Rate given Ideal Thrust calculator uses Mass Flow Rate = Ideal Thrust/(Exit Velocity-Flight Speed) to calculate the Mass Flow Rate, Mass Flow Rate given Ideal Thrust is a measurement of the rate of mass flow of a fluid, typically in aerospace engineering, calculated by considering the ideal thrust, the exit velocity and flight speed of an aircraft or rocket. Mass Flow Rate is denoted by m_a symbol.

How to calculate Mass Flow Rate given Ideal Thrust using this online calculator? To use this online calculator for Mass Flow Rate given Ideal Thrust, enter Ideal Thrust (T_ideal), Exit Velocity (V_e) & Flight Speed (V) and hit the calculate button. Here is how the Mass Flow Rate given Ideal Thrust calculation can be explained with given input values -> 3.306569 = 479.5/(248-111).

FAQ

What is Mass Flow Rate given Ideal Thrust?

Mass Flow Rate given Ideal Thrust is a measurement of the rate of mass flow of a fluid, typically in aerospace engineering, calculated by considering the ideal thrust, the exit velocity and flight speed of an aircraft or rocket and is represented as m_a = T_ideal/(V_e-V) or Mass Flow Rate = Ideal Thrust/(Exit Velocity-Flight Speed). Ideal Thrust is the thrust produced by an engine when nozzle exit pressure is same as ambient pressure or nozzle is perfectly expanded, 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 Mass Flow Rate given Ideal Thrust?

Mass Flow Rate given Ideal Thrust is a measurement of the rate of mass flow of a fluid, typically in aerospace engineering, calculated by considering the ideal thrust, the exit velocity and flight speed of an aircraft or rocket is calculated using Mass Flow Rate = Ideal Thrust/(Exit Velocity-Flight Speed). To calculate Mass Flow Rate given Ideal Thrust, you need Ideal Thrust (T_ideal), Exit Velocity (V_e) & Flight Speed (V). With our tool, you need to enter the respective value for Ideal Thrust, 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 Mass Flow Rate?

In this formula, Mass Flow Rate uses Ideal Thrust, Exit Velocity & Flight Speed. We can use 2 other way(s) to calculate the same, which is/are as follows -

Mass Flow Rate = Momentum of Ambient Air/Flight Speed
Mass Flow Rate = Ram Drag/Flight Speed

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