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)))
Pexit = Pc*((1+(Y-1)/2*M^2)^-(Y/(Y-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 of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a 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: 20 Megapascal --> 20000000 Pascal (Check conversion here)
Specific Heat Ratio: 1.392758 --> No Conversion Required
Mach Number: 1.4 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Pexit = Pc*((1+(Y-1)/2*M^2)^-(Y/(Y-1))) --> 20000000*((1+(1.392758-1)/2*1.4^2)^-(1.392758/(1.392758-1)))
Evaluating ... ...
Pexit = 6302943.3965282
STEP 3: Convert Result to Output's Unit
6302943.3965282 Pascal -->6.3029433965282 Megapascal (Check conversion here)
FINAL ANSWER
6.3029433965282 6.302943 Megapascal <-- Exit Pressure
(Calculation completed in 00.020 seconds)

Credits

Created by Shreyash
Rajiv Gandhi Institute of Technology (RGIT), Mumbai
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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]

Rocket Exit Pressure Formula

Exit Pressure = Chamber Pressure*((1+(Specific Heat Ratio-1)/2*Mach Number^2)^-(Specific Heat Ratio/(Specific Heat Ratio-1)))
Pexit = Pc*((1+(Y-1)/2*M^2)^-(Y/(Y-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, The Rocket Exit Pressure formula defines the exit pressure at an exhaust given that we know the total pressure and the Mach number. Exit Pressure is denoted by Pexit symbol.

How to calculate Rocket Exit Pressure using this online calculator? To use this online calculator for Rocket Exit Pressure, enter Chamber Pressure (Pc), Specific Heat Ratio (Y) & Mach Number (M) and hit the calculate button. Here is how the Rocket Exit Pressure calculation can be explained with given input values -> 6.3E-6 = 20000000*((1+(1.392758-1)/2*1.4^2)^-(1.392758/(1.392758-1))).

FAQ

What is Rocket Exit Pressure?
The Rocket Exit Pressure formula defines the exit pressure at an exhaust given that we know the total pressure and the Mach number and is represented as Pexit = Pc*((1+(Y-1)/2*M^2)^-(Y/(Y-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 of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a 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?
The Rocket Exit Pressure formula defines the exit pressure at an exhaust given that we know the total pressure and the Mach number 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 (Pc), Specific Heat Ratio (Y) & 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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