Rocket Exit Temperature Calculator

✖Chamber Temperature refers to the temperature of the combustion chamber in a propulsion system, such as a rocket or jet engine.ⓘ Chamber Temperature [T_c]			+10% -10%
✖The specific heat ratio describes the ratio of specific heats of a gas at constant pressure to that at constant volume.ⓘ Specific Heat Ratio [γ]			+10% -10%
✖Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.ⓘ Mach Number [M]			+10% -10%

✖Exit temperature is the degree of measure of heat at exit to the system.ⓘ Rocket Exit Temperature [T_exit]

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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
T_exit = T_c*(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

T_exit = T_c*(1+(γ-1)/2*M^2)^-1 --> 24.6*(1+(1.33-1)/2*1.4^2)^-1

Evaluating ... ...

T_exit = 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)

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Credits

Created by Shreyash

Rajiv Gandhi Institute of Technology (RGIT), Mumbai

Shreyash has created this Calculator and 10+ more calculators!

Verified by Anshika Arya

National Institute Of Technology (NIT), Hamirpur

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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

Rocket Exit Temperature Formula

LaTeX Go

Exit Temperature = Chamber Temperature*(1+(Specific Heat Ratio-1)/2*Mach Number^2)^-1
T_exit = T_c*(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, Rocket Exit Temperature formula is defined as a measure of the temperature of exhaust gases as they exit a rocket nozzle, which is crucial for understanding propulsion efficiency and performance in aerospace applications. Exit Temperature is denoted by T_exit symbol.

How to calculate Rocket Exit Temperature using this online calculator? To use this online calculator for Rocket Exit Temperature, enter Chamber Temperature (T_c), 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?

Rocket Exit Temperature formula is defined as a measure of the temperature of exhaust gases as they exit a rocket nozzle, which is crucial for understanding propulsion efficiency and performance in aerospace applications and is represented as T_exit = T_c*(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?

Rocket Exit Temperature formula is defined as a measure of the temperature of exhaust gases as they exit a rocket nozzle, which is crucial for understanding propulsion efficiency and performance in aerospace applications 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 (T_c), 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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