Thrust given Exhaust Velocity and Mass Flow Rate Calculator

✖Mass Flow Rate represents the amount of mass passing through a system per unit of time.ⓘ Mass Flow Rate [m_a]			+10% -10%
✖Exit Velocity is the speed at which exhaust gases exit the primary nozzle of a propulsion system, such as a rocket or jet engine.ⓘ Exit Velocity [C_j]			+10% -10%

✖Thrust is the force produced by the expulsion of high-speed exhaust gases from a rocket engine.ⓘ Thrust given Exhaust Velocity and Mass Flow Rate [F]

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Thrust given Exhaust Velocity and Mass Flow Rate Solution

STEP 0: Pre-Calculation Summary

Formula Used

Thrust = Mass Flow Rate*Exit Velocity
F = m_a*C_j
This formula uses 3 Variables

Variables Used

Thrust - (Measured in Newton) - Thrust is the force produced by the expulsion of high-speed exhaust gases from a rocket engine.
Mass Flow Rate - (Measured in Kilogram per Second) - Mass Flow Rate represents the amount of mass passing through a system per unit of time.
Exit Velocity - (Measured in Meter per Second) - Exit Velocity is the speed at which exhaust gases exit the primary nozzle of a propulsion system, such as a rocket or jet engine.

STEP 1: Convert Input(s) to Base Unit

Mass Flow Rate: 23.49 Kilogram per Second --> 23.49 Kilogram per Second No Conversion Required
Exit Velocity: 248 Meter per Second --> 248 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F = m_a*C_j --> 23.49*248

Evaluating ... ...

F = 5825.52

STEP 3: Convert Result to Output's Unit

5825.52 Newton --> No Conversion Required

FINAL ANSWER

5825.52 Newton <-- Thrust

(Calculation completed in 00.020 seconds)

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Created by Chilvera Bhanu Teja

Institute of Aeronautical Engineering (IARE), Hyderabad

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< Thrust and Power Generation Calculators

Power required to produce Exhaust Jet Velocity

LaTeX Go Power Required = 1/2*Mass Flow Rate*Exit Velocity^2

Thrust given Exhaust Velocity and Mass Flow Rate

LaTeX Go Thrust = Mass Flow Rate*Exit Velocity

Thrust given Mass and Acceleration of Rocket

LaTeX Go Thrust = Mass of Rocket*Acceleration

Acceleration of Rocket

LaTeX Go Acceleration = Thrust/Mass of Rocket

Thrust given Exhaust Velocity and Mass Flow Rate Formula

LaTeX Go

Thrust = Mass Flow Rate*Exit Velocity
F = m_a*C_j

What is thrust?

Thrust is a reaction force, When a system expels or accelerates mass in one direction, the accelerated mass will cause a force of equal magnitude but in opposite direction, to be applied to that system. The force applied on a surface in a direction perpendicular to the surface is also called thrust.

How to Calculate Thrust given Exhaust Velocity and Mass Flow Rate?

Thrust given Exhaust Velocity and Mass Flow Rate calculator uses Thrust = Mass Flow Rate*Exit Velocity to calculate the Thrust, Thrust given Exhaust Velocity and Mass Flow Rate formula is defined as a means to quantify the force produced by a rocket engine, based on the velocity of the exhaust gases and the rate at which mass is expelled. Thrust is denoted by F symbol.

How to calculate Thrust given Exhaust Velocity and Mass Flow Rate using this online calculator? To use this online calculator for Thrust given Exhaust Velocity and Mass Flow Rate, enter Mass Flow Rate (m_a) & Exit Velocity (C_j) and hit the calculate button. Here is how the Thrust given Exhaust Velocity and Mass Flow Rate calculation can be explained with given input values -> 5825.52 = 23.49*248.

FAQ

What is Thrust given Exhaust Velocity and Mass Flow Rate?

Thrust given Exhaust Velocity and Mass Flow Rate formula is defined as a means to quantify the force produced by a rocket engine, based on the velocity of the exhaust gases and the rate at which mass is expelled and is represented as F = m_a*C_j or Thrust = Mass Flow Rate*Exit Velocity. Mass Flow Rate represents the amount of mass passing through a system per unit of time & Exit Velocity is the speed at which exhaust gases exit the primary nozzle of a propulsion system, such as a rocket or jet engine.

How to calculate Thrust given Exhaust Velocity and Mass Flow Rate?

Thrust given Exhaust Velocity and Mass Flow Rate formula is defined as a means to quantify the force produced by a rocket engine, based on the velocity of the exhaust gases and the rate at which mass is expelled is calculated using Thrust = Mass Flow Rate*Exit Velocity. To calculate Thrust given Exhaust Velocity and Mass Flow Rate, you need Mass Flow Rate (m_a) & Exit Velocity (C_j). With our tool, you need to enter the respective value for Mass Flow Rate & Exit Velocity 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 Thrust?

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

Thrust = Mass of Rocket*Acceleration
Thrust = 1000*Power in Jet/[c]

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