Thrust given Mass and Acceleration of Rocket Solution

STEP 0: Pre-Calculation Summary
Formula Used
Thrust = Mass of Rocket*Acceleration
F = m*a
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 of Rocket - (Measured in Kilogram) - The Mass of Rocket is its stated mass at any given point in time while the rocket is in motion.
Acceleration - (Measured in Meter per Square Second) - Acceleration is the rate of change of velocity with respect to time.
STEP 1: Convert Input(s) to Base Unit
Mass of Rocket: 549054 Kilogram --> 549054 Kilogram No Conversion Required
Acceleration: 13.85 Meter per Square Second --> 13.85 Meter per Square Second No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
F = m*a --> 549054*13.85
Evaluating ... ...
F = 7604397.9
STEP 3: Convert Result to Output's Unit
7604397.9 Newton --> No Conversion Required
FINAL ANSWER
7604397.9 7.6E+6 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 Mass and Acceleration of Rocket Formula

Thrust = Mass of Rocket*Acceleration
F = m*a

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 Mass and Acceleration of Rocket?

Thrust given Mass and Acceleration of Rocket calculator uses Thrust = Mass of Rocket*Acceleration to calculate the Thrust, The Thrust given mass and acceleration of rocket formula is defined as the product of mass of rocket and acceleration of rocket. Thrust is denoted by F symbol.

How to calculate Thrust given Mass and Acceleration of Rocket using this online calculator? To use this online calculator for Thrust given Mass and Acceleration of Rocket, enter Mass of Rocket (m) & Acceleration (a) and hit the calculate button. Here is how the Thrust given Mass and Acceleration of Rocket calculation can be explained with given input values -> 7.604398 = 549054*13.85.

FAQ

What is Thrust given Mass and Acceleration of Rocket?
The Thrust given mass and acceleration of rocket formula is defined as the product of mass of rocket and acceleration of rocket and is represented as F = m*a or Thrust = Mass of Rocket*Acceleration. The Mass of Rocket is its stated mass at any given point in time while the rocket is in motion & Acceleration is the rate of change of velocity with respect to time.
How to calculate Thrust given Mass and Acceleration of Rocket?
The Thrust given mass and acceleration of rocket formula is defined as the product of mass of rocket and acceleration of rocket is calculated using Thrust = Mass of Rocket*Acceleration. To calculate Thrust given Mass and Acceleration of Rocket, you need Mass of Rocket (m) & Acceleration (a). With our tool, you need to enter the respective value for Mass of Rocket & Acceleration 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 of Rocket & Acceleration. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Thrust = 1000*Power in Jet/[c]
  • Thrust = Mass Flow Rate*Exit Velocity
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