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Rocket Exit Pressure Formula

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Exit Pressure is the pressure of the gases leaving the rocket nozzle. Check FAQs

P exit = P c \cdot ({(1 + \frac{γ - 1}{2} \cdot M^{2})}^{- (\frac{γ}{γ - 1})})

P_exit - Exit Pressure?P_c - Chamber Pressure?γ - Specific Heat Ratio?M - Mach Number?

Rocket Exit Pressure Example

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With units

Only example

Here is how the Rocket Exit Pressure equation looks like with Values.

Here is how the Rocket Exit Pressure equation looks like with Units.

Here is how the Rocket Exit Pressure equation looks like.

2.0979 = 6.49 \cdot ({(1 + \frac{1.33 - 1}{2} \cdot {1.4}^{2})}^{- (\frac{1.33}{1.33 - 1})})

2.0979MPa = 6.49MPa \cdot ({(1 + \frac{1.33 - 1}{2} \cdot {1.4}^{2})}^{- (\frac{1.33}{1.33 - 1})})

2.0979 = 6.49 \cdot ({(1 + \frac{1.33 - 1}{2} \cdot {1.4}^{2})}^{- (\frac{1.33}{1.33 - 1})})

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Rocket Exit Pressure Solution

Follow our step by step solution on how to calculate Rocket Exit Pressure?

FIRST Step Consider the formula

P exit = P c \cdot ({(1 + \frac{γ - 1}{2} \cdot M^{2})}^{- (\frac{γ}{γ - 1})})

Next Step Substitute values of Variables

∴

P exit = 6.49MPa \cdot ({(1 + \frac{1.33 - 1}{2} \cdot {1.4}^{2})}^{- (\frac{1.33}{1.33 - 1})})

Next Step Convert Units

∴

P exit = 6.5E+6Pa \cdot ({(1 + \frac{1.33 - 1}{2} \cdot {1.4}^{2})}^{- (\frac{1.33}{1.33 - 1})})

Next Step Prepare to Evaluate

∴

P exit = 6.5E+6 \cdot ({(1 + \frac{1.33 - 1}{2} \cdot {1.4}^{2})}^{- (\frac{1.33}{1.33 - 1})})

Next Step Evaluate

∴

P exit = 2097937.59491607Pa

Next Step Convert to Output's Unit

∴

P exit = 2.09793759491607MPa

LAST Step Rounding Answer

∴

P exit = 2.0979MPa

Rocket Exit Pressure Formula Elements

Variables

Exit Pressure

Exit Pressure is the pressure of the gases leaving the rocket nozzle.

Symbol: P_exit

Measurement: PressureUnit: MPa

Note: Value should be greater than 0.

Formulas to find Exit Pressure

Chamber Pressure

The Chamber Pressure is the amount of pressure generated inside the combustion chamber of a rocket.

Symbol: P_c

Measurement: PressureUnit: MPa

Note: Value should be greater than 0.

Formulas to find Chamber Pressure

Specific Heat Ratio

The specific heat ratio describes the ratio of specific heats of a gas at constant pressure to that at constant volume.

Symbol: γ

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Specific Heat Ratio

Mach Number

Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.

Symbol: M

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Mach Number

Other formulas in Thrust and Power Generation category

Go Power required to produce Exhaust Jet Velocity

P = \frac{1}{2} \cdot m a \cdot {C j}^{2}

Go Thrust given Exhaust Velocity and Mass Flow Rate

F = m a \cdot C j

Go Thrust given Mass and Acceleration of Rocket

F = m \cdot a

Go Acceleration of Rocket

a = \frac{F}{m}

How to Evaluate Rocket Exit Pressure?

Rocket Exit Pressure evaluator uses Exit Pressure = Chamber Pressure*((1+(Specific Heat Ratio-1)/2*Mach Number^2)^-(Specific Heat Ratio/(Specific Heat Ratio-1))) to evaluate 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 P_exit symbol.

How to evaluate Rocket Exit Pressure using this online evaluator? To use this online evaluator for Rocket Exit Pressure, enter Chamber Pressure (P_c), Specific Heat Ratio (γ) & Mach Number (M) and hit the calculate button.

FAQs on Rocket Exit Pressure

What is the formula to find Rocket Exit Pressure?

The formula of Rocket Exit Pressure is expressed as Exit Pressure = Chamber Pressure*((1+(Specific Heat Ratio-1)/2*Mach Number^2)^-(Specific Heat Ratio/(Specific Heat Ratio-1))). Here is an example- 2.1E-6 = 6490000*((1+(1.33-1)/2*1.4^2)^-(1.33/(1.33-1))).

How to calculate Rocket Exit Pressure?

With Chamber Pressure (P_c), Specific Heat Ratio (γ) & Mach Number (M) we can find Rocket Exit Pressure using the formula - Exit Pressure = Chamber Pressure*((1+(Specific Heat Ratio-1)/2*Mach Number^2)^-(Specific Heat Ratio/(Specific Heat Ratio-1))).

Can the Rocket Exit Pressure be negative?

No, the Rocket Exit Pressure, measured in Pressure cannot be negative.

Which unit is used to measure Rocket Exit Pressure?

Rocket Exit Pressure is usually measured using the Megapascal[MPa] for Pressure. Pascal[MPa], Kilopascal[MPa], Bar[MPa] are the few other units in which Rocket Exit Pressure can be measured.

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Rocket Exit Pressure Formula

Rocket Exit Pressure Example

Rocket Exit Pressure Solution

Rocket Exit Pressure Formula Elements

Other formulas in Thrust and Power Generation category

How to Evaluate Rocket Exit Pressure?

FAQs on Rocket Exit Pressure

Variable Name