Specific Volume at Throat Calculator

✖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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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 00.020 seconds)

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Credits

Created by LOKESH

Sri Ramakrishna Engineering College (SREC), COIMBATORE

LOKESH has created this Calculator and 25+ more calculators!

Verified by Harsh Raj

Indian Institute of Technology, Kharagpur (IIT KGP), West Bengal

Harsh Raj has verified this Calculator and 100+ more calculators!

< Nozzles Calculators

Characteristics Velocity

LaTeX Go Characteristics Velocity = sqrt((([R]*Temperature at Chamber)/Specific Heat Ratio)*((Specific Heat Ratio+1)/2)^((Specific Heat Ratio+1)/(Specific Heat Ratio-1)))

Propulsion Efficiency

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

Specific Volume at Throat

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

Specific Temperature at Throat

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

Specific Volume at Throat Formula

LaTeX Go

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, Specific Volume at Throat formula is defined as a measure of the volume occupied by a unit mass of gas at the throat of a rocket nozzle, which is crucial for understanding the flow characteristics and performance of rocket propulsion systems. 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?

Specific Volume at Throat formula is defined as a measure of the volume occupied by a unit mass of gas at the throat of a rocket nozzle, which is crucial for understanding the flow characteristics and performance of rocket propulsion systems 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?

Specific Volume at Throat formula is defined as a measure of the volume occupied by a unit mass of gas at the throat of a rocket nozzle, which is crucial for understanding the flow characteristics and performance of rocket propulsion systems 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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