Rocket Exit Temperature Solution

STEP 0: Pre-Calculation Summary
Formula Used
Exit Temperature = Chamber Temperature*(1+(Specific Heat Ratio-1)/2*Mach Number^2)^-1
Texit = Tc*(1+(γ-1)/2*M^2)^-1
This formula uses 4 Variables
Variables Used
Exit Temperature - (Measured in Kelvin) - Exit temperature is the degree of measure of heat at exit to the system.
Chamber Temperature - (Measured in Kelvin) - Chamber Temperature refers to the temperature of the combustion chamber in a propulsion system, such as a rocket or jet engine.
Specific Heat Ratio - The specific heat ratio describes the ratio of specific heats of a gas at constant pressure to that at constant volume.
Mach Number - Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.
STEP 1: Convert Input(s) to Base Unit
Chamber Temperature: 24.6 Kelvin --> 24.6 Kelvin No Conversion Required
Specific Heat Ratio: 1.33 --> No Conversion Required
Mach Number: 1.4 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Texit = Tc*(1+(γ-1)/2*M^2)^-1 --> 24.6*(1+(1.33-1)/2*1.4^2)^-1
Evaluating ... ...
Texit = 18.5884842073447
STEP 3: Convert Result to Output's Unit
18.5884842073447 Kelvin --> No Conversion Required
FINAL ANSWER
18.5884842073447 18.58848 Kelvin <-- Exit Temperature
(Calculation completed in 00.004 seconds)

Credits

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Created by Shreyash
Rajiv Gandhi Institute of Technology (RGIT), Mumbai
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National Institute Of Technology (NIT), Hamirpur
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​ LaTeX ​ Go Thrust = Mass Flow Rate*Exit Velocity
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Rocket Exit Temperature Formula

​LaTeX ​Go
Exit Temperature = Chamber Temperature*(1+(Specific Heat Ratio-1)/2*Mach Number^2)^-1
Texit = Tc*(1+(γ-1)/2*M^2)^-1

What is exit temperature?

Exit temperature in simple terms is the temperature at the exit of the rocket's nozzle. When exhaust gases flow from the combustion chamber to the nozzle, they experience a temperature change relative to the total temperature of the combustion chamber and its Mach number.

How to Calculate Rocket Exit Temperature?

Rocket Exit Temperature calculator uses Exit Temperature = Chamber Temperature*(1+(Specific Heat Ratio-1)/2*Mach Number^2)^-1 to calculate the Exit Temperature, The Rocket Exit Temperature formula defines the exit temperature at an exhaust, given that we know the total temperature and Mach number. Exit Temperature is denoted by Texit symbol.

How to calculate Rocket Exit Temperature using this online calculator? To use this online calculator for Rocket Exit Temperature, enter Chamber Temperature (Tc), Specific Heat Ratio (γ) & Mach Number (M) and hit the calculate button. Here is how the Rocket Exit Temperature calculation can be explained with given input values -> 18.13511 = 24.6*(1+(1.33-1)/2*1.4^2)^-1.

FAQ

What is Rocket Exit Temperature?
The Rocket Exit Temperature formula defines the exit temperature at an exhaust, given that we know the total temperature and Mach number and is represented as Texit = Tc*(1+(γ-1)/2*M^2)^-1 or Exit Temperature = Chamber Temperature*(1+(Specific Heat Ratio-1)/2*Mach Number^2)^-1. Chamber Temperature refers to the temperature of the combustion chamber in a propulsion system, such as a rocket or jet engine, The specific heat ratio describes the ratio of specific heats of a gas at constant pressure to that at constant volume & Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.
How to calculate Rocket Exit Temperature?
The Rocket Exit Temperature formula defines the exit temperature at an exhaust, given that we know the total temperature and Mach number is calculated using Exit Temperature = Chamber Temperature*(1+(Specific Heat Ratio-1)/2*Mach Number^2)^-1. To calculate Rocket Exit Temperature, you need Chamber Temperature (Tc), Specific Heat Ratio (γ) & Mach Number (M). With our tool, you need to enter the respective value for Chamber Temperature, Specific Heat Ratio & Mach Number and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
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