Specific Temperature at Throat Calculator

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Rocket Propulsion

Components of Gas Turbine

Jet Propulsion

Thermodynamics and Governing Equations

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✖Temperature at Chamber typically refers to the temperature inside a closed chamber or enclosure.ⓘ Temperature at Chamber [T₁]			+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 Temperature represents the temperature of the gas flowing through the throat per unit mass.ⓘ Specific Temperature at Throat [T_t]

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Formula

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Specific Temperature at Throat

Formula

`"T"_{"t"} = (2*"T"_{"1"})/("γ"+1)`

Example

`"219.7425K"=(2*"256K")/("1.33"+1)`

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Specific Temperature at Throat Solution

STEP 0: Pre-Calculation Summary

Formula Used

Specific Temperature = (2*Temperature at Chamber)/(Specific Heat Ratio+1)
T_t = (2*T₁)/(γ+1)
This formula uses 3 Variables

Variables Used

Specific Temperature - (Measured in Kelvin) - Specific Temperature represents the temperature of the gas flowing through the throat per unit mass.
Temperature at Chamber - (Measured in Kelvin) - Temperature at Chamber typically refers to the temperature inside a closed chamber or enclosure.
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

Temperature at Chamber: 256 Kelvin --> 256 Kelvin No Conversion Required
Specific Heat Ratio: 1.33 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

T_t = (2*T₁)/(γ+1) --> (2*256)/(1.33+1)

Evaluating ... ...

T_t = 219.742489270386

STEP 3: Convert Result to Output's Unit

219.742489270386 Kelvin --> No Conversion Required

FINAL ANSWER

219.742489270386 ≈ 219.7425 Kelvin <-- Specific Temperature

(Calculation completed in 00.004 seconds)

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Created by LOKESH

Sri Ramakrishna Engineering College (SREC), COIMBATORE

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

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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 Temperature at Throat Formula

Specific Temperature = (2*Temperature at Chamber)/(Specific Heat Ratio+1)
T_t = (2*T₁)/(γ+1)

What is Temperature at Throat ?

The temperature at the throat of a rocket nozzle, is a crucial parameter in rocket propulsion engineering. It represents the temperature of the fluid (usually a gas) at the narrowest point of the nozzle where the flow velocity is at its maximum.

How to Calculate Specific Temperature at Throat?

Specific Temperature at Throat calculator uses Specific Temperature = (2*Temperature at Chamber)/(Specific Heat Ratio+1) to calculate the Specific Temperature, Specific Temperature at Throat represents the temperature at the throat of the nozzle.this equation provides a simple relationship between the temperature at the nozzle inlet and the temperature at the throat of the nozzle, taking into account the specific heat ratio of the gas. Specific Temperature is denoted by T_t symbol.

How to calculate Specific Temperature at Throat using this online calculator? To use this online calculator for Specific Temperature at Throat, enter Temperature at Chamber (T₁) & Specific Heat Ratio (γ) and hit the calculate button. Here is how the Specific Temperature at Throat calculation can be explained with given input values -> 219.7425 = (2*256)/(1.33+1).

FAQ

What is Specific Temperature at Throat?

Specific Temperature at Throat represents the temperature at the throat of the nozzle.this equation provides a simple relationship between the temperature at the nozzle inlet and the temperature at the throat of the nozzle, taking into account the specific heat ratio of the gas and is represented as T_t = (2*T₁)/(γ+1) or Specific Temperature = (2*Temperature at Chamber)/(Specific Heat Ratio+1). Temperature at Chamber typically refers to the temperature inside a closed chamber or enclosure & 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 Temperature at Throat?

Specific Temperature at Throat represents the temperature at the throat of the nozzle.this equation provides a simple relationship between the temperature at the nozzle inlet and the temperature at the throat of the nozzle, taking into account the specific heat ratio of the gas is calculated using Specific Temperature = (2*Temperature at Chamber)/(Specific Heat Ratio+1). To calculate Specific Temperature at Throat, you need Temperature at Chamber (T₁) & Specific Heat Ratio (γ). With our tool, you need to enter the respective value for Temperature at Chamber & 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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