Exit Velocity given Molar Mass 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%
✖Molar Mass is the mass of a given substance divided by the amount of substance.ⓘ Molar Mass [M_molar]			+10% -10%
✖Exit Pressure is the pressure of the gases leaving the rocket nozzle.ⓘ Exit Pressure [P_exit]			+10% -10%
✖The Chamber Pressure is the amount of pressure generated inside the combustion chamber of a rocket.ⓘ Chamber Pressure [P_c]			+10% -10%

✖Exit Velocity is the speed at which exhaust gases exit the primary nozzle of a propulsion system, such as a rocket or jet engine.ⓘ Exit Velocity given Molar Mass [C_j]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Rocket Propulsion Formulas PDF PDF Image

Exit Velocity given Molar Mass Solution

STEP 0: Pre-Calculation Summary

Formula Used

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)))
C_j = sqrt(((2*T_c*[R]*γ)/(M_molar)/(γ-1))*(1-(P_exit/P_c)^(1-1/γ)))
This formula uses 1 Constants, 1 Functions, 6 Variables

Constants Used

[R] - Universal gas constant Value Taken As 8.31446261815324

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Exit Velocity - (Measured in Meter per Second) - Exit Velocity is the speed at which exhaust gases exit the primary nozzle of a propulsion system, such as a rocket or jet engine.
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.
Molar Mass - (Measured in Kilogram Per Mole) - Molar Mass is the mass of a given substance divided by the amount of substance.
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.

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
Molar Mass: 6.5 Gram Per Mole --> 0.0065 Kilogram Per Mole (Check conversion here)
Exit Pressure: 2.1 Megapascal --> 2100000 Pascal (Check conversion here)
Chamber Pressure: 6.49 Megapascal --> 6490000 Pascal (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_j = sqrt(((2*T_c*[R]*γ)/(M_molar)/(γ-1))*(1-(P_exit/P_c)^(1-1/γ))) --> sqrt(((2*24.6*[R]*1.33)/(0.0065)/(1.33-1))*(1-(2100000/6490000)^(1-1/1.33)))

Evaluating ... ...

C_j = 248.869960344833

STEP 3: Convert Result to Output's Unit

248.869960344833 Meter per Second --> No Conversion Required

FINAL ANSWER

248.869960344833 ≈ 248.87 Meter per Second <-- Exit Velocity

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Propulsion » Rocket Propulsion » Aerospace » Thrust and Power Generation » Exit Velocity given Molar Mass

Credits

Created by Shreyash

Rajiv Gandhi Institute of Technology (RGIT), Mumbai

Shreyash has created this Calculator and 10+ more calculators!

Verified by Kartikay Pandit

National Institute Of Technology (NIT), Hamirpur

Kartikay Pandit has verified this Calculator and 400+ more calculators!

< 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

Exit Velocity given Molar Mass Formula

LaTeX Go

What is Exit Velocity?

The velocity produced at the outlet of the rocket engine through the nozzle is called as exit velocity. This parameter is useful to examine the rocket's performance.

How to Calculate Exit Velocity given Molar Mass?

Exit Velocity given Molar Mass calculator uses 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))) to calculate the Exit Velocity, Exit Velocity given Molar Mass formula is defined as a method to determine the speed at which exhaust gases exit a propulsion system, taking into account the molar mass of the gases and the thermodynamic properties of the system. Exit Velocity is denoted by C_j symbol.

How to calculate Exit Velocity given Molar Mass using this online calculator? To use this online calculator for Exit Velocity given Molar Mass, enter Chamber Temperature (T_c), Specific Heat Ratio (γ), Molar Mass (M_molar), Exit Pressure (P_exit) & Chamber Pressure (P_c) and hit the calculate button. Here is how the Exit Velocity given Molar Mass calculation can be explained with given input values -> 249.017 = sqrt(((2*24.6*[R]*1.33)/(0.0065)/(1.33-1))*(1-(2100000/6490000)^(1-1/1.33))).

FAQ

What is Exit Velocity given Molar Mass?

Exit Velocity given Molar Mass formula is defined as a method to determine the speed at which exhaust gases exit a propulsion system, taking into account the molar mass of the gases and the thermodynamic properties of the system and is represented as C_j = sqrt(((2*T_c*[R]*γ)/(M_molar)/(γ-1))*(1-(P_exit/P_c)^(1-1/γ))) or 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))). 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, Molar Mass is the mass of a given substance divided by the amount of substance, Exit Pressure is the pressure of the gases leaving the rocket nozzle & The Chamber Pressure is the amount of pressure generated inside the combustion chamber of a rocket.

How to calculate Exit Velocity given Molar Mass?

Exit Velocity given Molar Mass formula is defined as a method to determine the speed at which exhaust gases exit a propulsion system, taking into account the molar mass of the gases and the thermodynamic properties of the system is calculated using 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))). To calculate Exit Velocity given Molar Mass, you need Chamber Temperature (T_c), Specific Heat Ratio (γ), Molar Mass (M_molar), Exit Pressure (P_exit) & Chamber Pressure (P_c). With our tool, you need to enter the respective value for Chamber Temperature, Specific Heat Ratio, Molar Mass, Exit Pressure & Chamber Pressure 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 Exit Velocity?

In this formula, Exit Velocity uses Chamber Temperature, Specific Heat Ratio, Molar Mass, Exit Pressure & Chamber Pressure. We can use 2 other way(s) to calculate the same, which is/are as follows -

Exit Velocity = Mach Number*sqrt(Specific Heat Ratio*[R]/Molar Mass*Exit Temperature)
Exit Velocity = sqrt(2*Total Temperature*Molar Specific Heat Capacity at Constant Pressure*(1-(Exit Pressure/Chamber Pressure)^(1-1/Specific Heat Ratio)))

Home

FREE PDFs

🔍 Search