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Throat Velocity of Nozzle Formula

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The throat velocity in rocketry refers to the velocity of the gases passing through the throat of the rocket engine nozzle. Check FAQs

v t = \sqrt{\frac{2 \cdot γ}{γ + 1} \cdot [R] \cdot T 1}

v_t - Throat Velocity?γ - Specific Heat Ratio?T₁ - Temperature at Chamber?[R] - Universal gas constant?

Throat Velocity of Nozzle Example

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Here is how the Throat Velocity of Nozzle equation looks like with Values.

Here is how the Throat Velocity of Nozzle equation looks like with Units.

Here is how the Throat Velocity of Nozzle equation looks like.

49.2947 = \sqrt{\frac{2 \cdot 1.33}{1.33 + 1} \cdot 8.3145 \cdot 256}

49.2947m/s = \sqrt{\frac{2 \cdot 1.33}{1.33 + 1} \cdot 8.3145 \cdot 256K}

49.2947 = \sqrt{\frac{2 \cdot 1.33}{1.33 + 1} \cdot 8.3145 \cdot 256}

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Throat Velocity of Nozzle Solution

Follow our step by step solution on how to calculate Throat Velocity of Nozzle?

FIRST Step Consider the formula

v t = \sqrt{\frac{2 \cdot γ}{γ + 1} \cdot [R] \cdot T 1}

Next Step Substitute values of Variables

∴

v t = \sqrt{\frac{2 \cdot 1.33}{1.33 + 1} \cdot [R] \cdot 256K}

Next Step Substitute values of Constants

∴

v t = \sqrt{\frac{2 \cdot 1.33}{1.33 + 1} \cdot 8.3145 \cdot 256K}

Next Step Prepare to Evaluate

∴

v t = \sqrt{\frac{2 \cdot 1.33}{1.33 + 1} \cdot 8.3145 \cdot 256}

Next Step Evaluate

∴

v t = 49.2946665252529m/s

LAST Step Rounding Answer

∴

v t = 49.2947m/s

Throat Velocity of Nozzle Formula Elements

Variables

Constants

Functions

Throat Velocity

The throat velocity in rocketry refers to the velocity of the gases passing through the throat of the rocket engine nozzle.

Symbol: v_t

Measurement: SpeedUnit: m/s

Note: Value should be greater than 0.

Formulas to find Throat Velocity

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

Temperature at Chamber

Temperature at Chamber typically refers to the temperature inside a closed chamber or enclosure.

Symbol: T₁

Measurement: TemperatureUnit: K

Note: Value should be greater than 0.

Formulas to find Temperature at Chamber

Universal gas constant

Universal gas constant is a fundamental physical constant that appears in the ideal gas law, relating the pressure, volume, and temperature of an ideal gas.

Symbol: [R]

Value: 8.31446261815324

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.

Syntax: sqrt(Number)

Other formulas in Theory Of Rockets category

Go Total Velocity Required to Place Satellite in Orbit

V T = \sqrt{\frac{[G.] \cdot M E \cdot (R E + 2 \cdot h)}{R E \cdot (R E + h)}}

Go Velocity Increment of Rocket

ΔV = V e \cdot \ln (\frac{m i}{m final})

Go Rocket Exhaust Gas Velocity

V e = \sqrt{(\frac{2 \cdot γ}{γ - 1}) \cdot [R] \cdot T 1 \cdot (1 - {(\frac{p 2}{p 1})}^{\frac{γ - 1}{γ}})}

Go Structural Mass Fraction

σ = \frac{m s}{m p + m s}

How to Evaluate Throat Velocity of Nozzle?

Throat Velocity of Nozzle evaluator uses Throat Velocity = sqrt((2*Specific Heat Ratio)/(Specific Heat Ratio+1)*[R]*Temperature at Chamber) to evaluate the Throat Velocity, The Throat Velocity of Nozzle refers to the velocity of the exhaust gases as they pass through the narrowest section of the rocket engine nozzle, it is a crucial parameter in rocket engine design as it determines the maximum velocity of the exhaust gases at the throat. Throat Velocity is denoted by v_t symbol.

How to evaluate Throat Velocity of Nozzle using this online evaluator? To use this online evaluator for Throat Velocity of Nozzle, enter Specific Heat Ratio (γ) & Temperature at Chamber (T₁) and hit the calculate button.

FAQs on Throat Velocity of Nozzle

What is the formula to find Throat Velocity of Nozzle?

The formula of Throat Velocity of Nozzle is expressed as Throat Velocity = sqrt((2*Specific Heat Ratio)/(Specific Heat Ratio+1)*[R]*Temperature at Chamber). Here is an example- 49.29467 = sqrt((2*1.33)/(1.33+1)*[R]*256).

How to calculate Throat Velocity of Nozzle?

With Specific Heat Ratio (γ) & Temperature at Chamber (T₁) we can find Throat Velocity of Nozzle using the formula - Throat Velocity = sqrt((2*Specific Heat Ratio)/(Specific Heat Ratio+1)*[R]*Temperature at Chamber). This formula also uses Universal gas constant and Square Root (sqrt) function(s).

Can the Throat Velocity of Nozzle be negative?

No, the Throat Velocity of Nozzle, measured in Speed cannot be negative.

Which unit is used to measure Throat Velocity of Nozzle?

Throat Velocity of Nozzle is usually measured using the Meter per Second[m/s] for Speed. Meter per Minute[m/s], Meter per Hour[m/s], Kilometer per Hour[m/s] are the few other units in which Throat Velocity of Nozzle can be measured.

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Throat Velocity of Nozzle Formula

Throat Velocity of Nozzle Example

Throat Velocity of Nozzle Solution

Throat Velocity of Nozzle Formula Elements

Other formulas in Theory Of Rockets category

How to Evaluate Throat Velocity of Nozzle?

FAQs on Throat Velocity of Nozzle

Variable Name