Specific Volume at Throat Formula

Fx Copy
LaTeX Copy
Specific Volume represents the volume occupied by a unit mass of propellant at the throat conditions. Check FAQs
Vt=V1(γ+12)1γ-1
Vt - Specific Volume?V1 - Inlet Volume?γ - Specific Heat Ratio?

Specific Volume at Throat Example

With values
With units
Only example

Here is how the Specific Volume at Throat equation looks like with Values.

Here is how the Specific Volume at Throat equation looks like with Units.

Here is how the Specific Volume at Throat equation looks like.

10.0076Edit=6.3Edit(1.33Edit+12)11.33Edit-1
You are here -
HomeIcon Home » Category Physics » Category Aerospace » Category Propulsion » fx Specific Volume at Throat

Specific Volume at Throat Solution

Follow our step by step solution on how to calculate Specific Volume at Throat?

FIRST Step Consider the formula
Vt=V1(γ+12)1γ-1
Next Step Substitute values of Variables
Vt=6.3(1.33+12)11.33-1
Next Step Prepare to Evaluate
Vt=6.3(1.33+12)11.33-1
Next Step Evaluate
Vt=10.0075599880739
LAST Step Rounding Answer
Vt=10.0076

Specific Volume at Throat Formula Elements

Variables
Specific Volume
Specific Volume represents the volume occupied by a unit mass of propellant at the throat conditions.
Symbol: Vt
Measurement: VolumeUnit:
Note: Value should be greater than 0.
Inlet Volume
The inlet volume typically refers to the volume of fluid (propellant mixture) entering a system.
Symbol: V1
Measurement: VolumeUnit:
Note: Value should be greater than 0.
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.

Other formulas in Nozzles category

​Go Propulsion Efficiency
ηprop=2(v0v9)1+(v0v9)2
​Go Specific Temperature at Throat
Tt=2T1γ+1
​Go Characteristics Velocity
C=([R]T1γ)(γ+12)γ+1γ-1
​Go Nozzle Thrust Coefficient
CF=FAtP1

How to Evaluate Specific Volume at Throat?

Specific Volume at Throat evaluator uses Specific Volume = Inlet Volume*((Specific Heat Ratio+1)/2)^(1/(Specific Heat Ratio-1)) to evaluate the Specific Volume, The specific volume at throat of a rocket nozzle represents the volume occupied by a unit mass of propellant at that specific location, this formula provides a simplified relationship between the specific volume at the throat and the specific volume at the nozzle exit, taking into account the properties of the gas and the flow conditions within the rocket nozzle. Specific Volume is denoted by Vt symbol.

How to evaluate Specific Volume at Throat using this online evaluator? To use this online evaluator for Specific Volume at Throat, enter Inlet Volume (V1) & Specific Heat Ratio (γ) and hit the calculate button.

FAQs on Specific Volume at Throat

What is the formula to find Specific Volume at Throat?
The formula of Specific Volume at Throat is expressed as Specific Volume = Inlet Volume*((Specific Heat Ratio+1)/2)^(1/(Specific Heat Ratio-1)). Here is an example- 10.00756 = 6.3*((1.33+1)/2)^(1/(1.33-1)).
How to calculate Specific Volume at Throat?
With Inlet Volume (V1) & Specific Heat Ratio (γ) we can find Specific Volume at Throat using the formula - Specific Volume = Inlet Volume*((Specific Heat Ratio+1)/2)^(1/(Specific Heat Ratio-1)).
Can the Specific Volume at Throat be negative?
No, the Specific Volume at Throat, measured in Volume cannot be negative.
Which unit is used to measure Specific Volume at Throat?
Specific Volume at Throat is usually measured using the Cubic Meter[m³] for Volume. Cubic Centimeter[m³], Cubic Millimeter[m³], Liter[m³] are the few other units in which Specific Volume at Throat can be measured.
Copied!