Rocket Exit Pressure Calculator

✖The Chamber Pressure is the amount of pressure generated inside the combustion chamber of a rocket.ⓘ Chamber Pressure [P_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 Pressure is the pressure of the gases leaving the rocket nozzle.ⓘ Rocket Exit Pressure [P_exit]

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Rocket Exit Pressure Solution

STEP 0: Pre-Calculation Summary

Formula Used

Exit Pressure = Chamber Pressure*((1+(Specific Heat Ratio-1)/2*Mach Number^2)^-(Specific Heat Ratio/(Specific Heat Ratio-1)))
P_exit = P_c*((1+(γ-1)/2*M^2)^-(γ/(γ-1)))
This formula uses 4 Variables

Variables Used

Exit Pressure - (Measured in Pascal) - Exit Pressure is the pressure of the gases leaving the rocket nozzle.
Chamber Pressure - (Measured in Pascal) - The Chamber Pressure is the amount of pressure generated inside the combustion chamber of a rocket.
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 Pressure: 6.49 Megapascal --> 6490000 Pascal (Check conversion here)
Specific Heat Ratio: 1.33 --> No Conversion Required
Mach Number: 1.4 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

P_exit = P_c*((1+(γ-1)/2*M^2)^-(γ/(γ-1))) --> 6490000*((1+(1.33-1)/2*1.4^2)^-(1.33/(1.33-1)))

Evaluating ... ...

P_exit = 2097937.59491607

STEP 3: Convert Result to Output's Unit

2097937.59491607 Pascal -->2.09793759491607 Megapascal (Check conversion here)

FINAL ANSWER

2.09793759491607 ≈ 2.097938 Megapascal <-- Exit Pressure

(Calculation completed in 00.007 seconds)

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Created by Shreyash

Rajiv Gandhi Institute of Technology (RGIT), Mumbai

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Verified by Kartikay Pandit

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 Pressure Formula

LaTeX Go

Exit Pressure = Chamber Pressure*((1+(Specific Heat Ratio-1)/2*Mach Number^2)^-(Specific Heat Ratio/(Specific Heat Ratio-1)))
P_exit = P_c*((1+(γ-1)/2*M^2)^-(γ/(γ-1)))

What is exit pressure?

The pressure generated at the exit of the nozzle is called as eit pressure. When exhaust gases flow from combustion chamber to the nozzle, the airflow changes depending upon the size and shape of the nozzle, thus bringing a change in the outlet pressure. It relates to the total pressure available in the combustion chamber and the Mach number.

How to Calculate Rocket Exit Pressure?

Rocket Exit Pressure calculator uses Exit Pressure = Chamber Pressure*((1+(Specific Heat Ratio-1)/2*Mach Number^2)^-(Specific Heat Ratio/(Specific Heat Ratio-1))) to calculate the Exit Pressure, Rocket Exit Pressure formula is defined as a measure of the pressure at the exit of a rocket nozzle, which is influenced by the chamber pressure and the characteristics of the exhaust gases, impacting propulsion efficiency. Exit Pressure is denoted by P_exit symbol.

How to calculate Rocket Exit Pressure using this online calculator? To use this online calculator for Rocket Exit Pressure, enter Chamber Pressure (P_c), Specific Heat Ratio (γ) & Mach Number (M) and hit the calculate button. Here is how the Rocket Exit Pressure calculation can be explained with given input values -> 2.1E-6 = 6490000*((1+(1.33-1)/2*1.4^2)^-(1.33/(1.33-1))).

FAQ

What is Rocket Exit Pressure?

Rocket Exit Pressure formula is defined as a measure of the pressure at the exit of a rocket nozzle, which is influenced by the chamber pressure and the characteristics of the exhaust gases, impacting propulsion efficiency and is represented as P_exit = P_c*((1+(γ-1)/2*M^2)^-(γ/(γ-1))) or Exit Pressure = Chamber Pressure*((1+(Specific Heat Ratio-1)/2*Mach Number^2)^-(Specific Heat Ratio/(Specific Heat Ratio-1))). The Chamber Pressure is the amount of pressure generated inside the combustion chamber of a rocket, 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 Pressure?

Rocket Exit Pressure formula is defined as a measure of the pressure at the exit of a rocket nozzle, which is influenced by the chamber pressure and the characteristics of the exhaust gases, impacting propulsion efficiency is calculated using Exit Pressure = Chamber Pressure*((1+(Specific Heat Ratio-1)/2*Mach Number^2)^-(Specific Heat Ratio/(Specific Heat Ratio-1))). To calculate Rocket Exit Pressure, you need Chamber Pressure (P_c), Specific Heat Ratio (γ) & Mach Number (M). With our tool, you need to enter the respective value for Chamber Pressure, 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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