Thrust given Exhaust Velocity and Mass Flow Rate Solution

STEP 0: Pre-Calculation Summary
Formula Used
Thrust = Mass Flow Rate*Exit Velocity
F = ma*Cj
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: 2.51 Kilogram per Second --> 2.51 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 = ma*Cj --> 2.51*248
Evaluating ... ...
F = 622.48
STEP 3: Convert Result to Output's Unit
622.48 Newton --> No Conversion Required
FINAL ANSWER
622.48 Newton <-- Thrust
(Calculation completed in 00.004 seconds)

Credits

Created by Chilvera Bhanu Teja
Institute of Aeronautical Engineering (IARE), Hyderabad
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National Institute of Technology (NIT), Tiruchirapalli
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14 Rocket Propulsion Calculators

Mass Flow Rate through Engine
Go Mass Flow Rate = Mach Number*Area*Total Pressure*sqrt(Specific Heat Ratio*Molar Mass/(Total Temperature*[R]))*(1+(Specific Heat Ratio-1)* Mach Number^2/2)^(-(Specific Heat Ratio+1)/(2*Specific Heat Ratio-2))
Exit Velocity given Molar Mass
Go Exit Velocity = sqrt(((2*Chamber Temperature*[R]*Specific Heat Ratio)/(Molar Mass)/(Specific Heat Ratio-1))*(1-(Exit Pressure/Chamber Pressure)^(1-1/Specific Heat Ratio)))
Compressible Area Ratio
Go Area Ratio = ((Specific Heat Ratio+1)/2)^(-(Specific Heat Ratio+1)/(2*Specific Heat Ratio-2))*((1+(Specific Heat Ratio-1)/2*Mach Number^2)^((Specific Heat Ratio+1)/(2*Specific Heat Ratio-2)))/Mach Number
Exit Velocity given Molar Specific Heat Capacity
Go Exit Velocity = sqrt(2*Total Temperature*Molar Specific Heat Capacity at Constant Pressure*(1-(Exit Pressure/Chamber Pressure)^(1-1/Specific Heat Ratio)))
Rocket Exit Pressure
Go Exit Pressure = Chamber Pressure*((1+(Specific Heat Ratio-1)/2*Mach Number^2)^-(Specific Heat Ratio/(Specific Heat Ratio-1)))
Exit Velocity given Mach Number and Exit Temperature
Go Exit Velocity = Mach Number*sqrt(Specific Heat Ratio*[R]/Molar Mass*Exit Temperature)
Rocket Exit Temperature
Go Exit Temperature = Chamber Temperature*(1+(Specific Heat Ratio-1)/2*Mach Number^2)^-1
Total Impulse
Go Total impulse = int(Thrust,x,Initial time,Final time)
Power required to produce Exhaust Jet Velocity given Mass of Rocket and Acceleration
Go Power Required = (Mass of Rocket*Acceleration*Effective Exhaust Velocity)/2
Power required to produce Exhaust Jet Velocity
Go Power Required = 1/2*Mass Flow Rate*Exit Velocity^2
Thrust given Exhaust Velocity and Mass Flow Rate
Go Thrust = Mass Flow Rate*Exit Velocity
Thrust given Mass and Acceleration of Rocket
Go Thrust = Mass of Rocket*Acceleration
Acceleration of Rocket
Go Acceleration = Thrust/Mass of Rocket
Photon Propulsion Thrust
Go Thrust = 1000*Power in Jet/[c]

Thrust given Exhaust Velocity and Mass Flow Rate Formula

Thrust = Mass Flow Rate*Exit Velocity
F = ma*Cj

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, The Thrust given exhaust velocity and mass flow rate formula is defined as the product of mass flow rate of air and aircraft jet velocity. 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 (ma) & Exit Velocity (Cj) 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 -> 0.000622 = 2.51*248.

FAQ

What is Thrust given Exhaust Velocity and Mass Flow Rate?
The Thrust given exhaust velocity and mass flow rate formula is defined as the product of mass flow rate of air and aircraft jet velocity and is represented as F = ma*Cj 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?
The Thrust given exhaust velocity and mass flow rate formula is defined as the product of mass flow rate of air and aircraft jet velocity is calculated using Thrust = Mass Flow Rate*Exit Velocity. To calculate Thrust given Exhaust Velocity and Mass Flow Rate, you need Mass Flow Rate (ma) & Exit Velocity (Cj). 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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