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)))
Cj = sqrt(((2*Tc*[R]*γ)/(Mmolar)/(γ-1))*(1-(Pexit/Pc)^(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
Cj = sqrt(((2*Tc*[R]*γ)/(Mmolar)/(γ-1))*(1-(Pexit/Pc)^(1-1/γ))) --> sqrt(((2*24.6*[R]*1.33)/(0.0065)/(1.33-1))*(1-(2100000/6490000)^(1-1/1.33)))
Evaluating ... ...
Cj = 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)

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Rajiv Gandhi Institute of Technology (RGIT), Mumbai
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Exit Velocity given Molar Mass Formula

​LaTeX ​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)))
Cj = sqrt(((2*Tc*[R]*γ)/(Mmolar)/(γ-1))*(1-(Pexit/Pc)^(1-1/γ)))

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, The Exit Velocity given Molar Mass formula can be used to determine the exit velocity through the nozzle when the value of Molar Mass is known. Exit Velocity is denoted by Cj 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 (Tc), Specific Heat Ratio (γ), Molar Mass (Mmolar), Exit Pressure (Pexit) & Chamber Pressure (Pc) 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?
The Exit Velocity given Molar Mass formula can be used to determine the exit velocity through the nozzle when the value of Molar Mass is known and is represented as Cj = sqrt(((2*Tc*[R]*γ)/(Mmolar)/(γ-1))*(1-(Pexit/Pc)^(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?
The Exit Velocity given Molar Mass formula can be used to determine the exit velocity through the nozzle when the value of Molar Mass is known 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 (Tc), Specific Heat Ratio (γ), Molar Mass (Mmolar), Exit Pressure (Pexit) & Chamber Pressure (Pc). 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)))
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