Specific Volume at Throat Calculator

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Rocket Propulsion

Components of Gas Turbine

Jet Propulsion

Thermodynamics and Governing Equations

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✖The inlet volume typically refers to the volume of fluid (propellant mixture) entering a system.ⓘ Inlet Volume [V₁]			+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%

✖Specific Volume represents the volume occupied by a unit mass of propellant at the throat conditions.ⓘ Specific Volume at Throat [V_t]

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Formula

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Specific Volume at Throat

Formula

`"V"_{"t"} = "V"_{"1"}*(("γ"+1)/2)^(1/("γ"-1))`

Example

`"10.00756m³"="6.3m³"*(("1.33"+1)/2)^(1/("1.33"-1))`

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Specific Volume at Throat Solution

STEP 0: Pre-Calculation Summary

Formula Used

Specific Volume = Inlet Volume*((Specific Heat Ratio+1)/2)^(1/(Specific Heat Ratio-1))
V_t = V₁*((γ+1)/2)^(1/(γ-1))
This formula uses 3 Variables

Variables Used

Specific Volume - (Measured in Cubic Meter) - Specific Volume represents the volume occupied by a unit mass of propellant at the throat conditions.
Inlet Volume - (Measured in Cubic Meter) - The inlet volume typically refers to the volume of fluid (propellant mixture) entering a system.
Specific Heat Ratio - The specific heat ratio describes the ratio of specific heats of a gas at constant pressure to that at constant volume.

STEP 1: Convert Input(s) to Base Unit

Inlet Volume: 6.3 Cubic Meter --> 6.3 Cubic Meter No Conversion Required
Specific Heat Ratio: 1.33 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V_t = V₁*((γ+1)/2)^(1/(γ-1)) --> 6.3*((1.33+1)/2)^(1/(1.33-1))

Evaluating ... ...

V_t = 10.0075599880739

STEP 3: Convert Result to Output's Unit

10.0075599880739 Cubic Meter --> No Conversion Required

FINAL ANSWER

10.0075599880739 ≈ 10.00756 Cubic Meter <-- Specific Volume

(Calculation completed in 00.004 seconds)

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< 3 Nozzles Calculators

Propulsion Efficiency

Go Propulsion Efficiency = (2*(Vehicle Speed/Exhaust Speed))/(1+(Vehicle Speed/Exhaust Speed)^2)

Specific Volume at Throat

Go Specific Volume = Inlet Volume*((Specific Heat Ratio+1)/2)^(1/(Specific Heat Ratio-1))

Specific Temperature at Throat

Go Specific Temperature = (2*Temperature at Chamber)/(Specific Heat Ratio+1)

Specific Volume at Throat Formula

Specific Volume = Inlet Volume*((Specific Heat Ratio+1)/2)^(1/(Specific Heat Ratio-1))
V_t = V₁*((γ+1)/2)^(1/(γ-1))

What is Specific Volume ?

Specific volume is a thermodynamic property of a substance, defined as the volume occupied by a unit mass of the substance. Specific volume is essentially a measure of how much space a unit mass of a substance occupies.

How to Calculate Specific Volume at Throat?

Specific Volume at Throat calculator uses Specific Volume = Inlet Volume*((Specific Heat Ratio+1)/2)^(1/(Specific Heat Ratio-1)) to calculate 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 V_t symbol.

How to calculate Specific Volume at Throat using this online calculator? To use this online calculator for Specific Volume at Throat, enter Inlet Volume (V₁) & Specific Heat Ratio (γ) and hit the calculate button. Here is how the Specific Volume at Throat calculation can be explained with given input values -> 10.00756 = 6.3*((1.33+1)/2)^(1/(1.33-1)).

FAQ

What is Specific Volume at Throat?

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 and is represented as V_t = V₁*((γ+1)/2)^(1/(γ-1)) or Specific Volume = Inlet Volume*((Specific Heat Ratio+1)/2)^(1/(Specific Heat Ratio-1)). The inlet volume typically refers to the volume of fluid (propellant mixture) entering a system & The specific heat ratio describes the ratio of specific heats of a gas at constant pressure to that at constant volume.

How to calculate Specific Volume at Throat?

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 is calculated using Specific Volume = Inlet Volume*((Specific Heat Ratio+1)/2)^(1/(Specific Heat Ratio-1)). To calculate Specific Volume at Throat, you need Inlet Volume (V₁) & Specific Heat Ratio (γ). With our tool, you need to enter the respective value for Inlet Volume & Specific Heat Ratio and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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