Specific Temperature at Throat Calculator

✖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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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 00.020 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 Temperature at Throat Formula

LaTeX Go

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 formula is defined as a measure of the temperature at the throat of a rocket nozzle, which is crucial for understanding the thermodynamic performance and efficiency of rocket propulsion systems. 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 formula is defined as a measure of the temperature at the throat of a rocket nozzle, which is crucial for understanding the thermodynamic performance and efficiency of rocket propulsion systems 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 formula is defined as a measure of the temperature at the throat of a rocket nozzle, which is crucial for understanding the thermodynamic performance and efficiency of rocket propulsion systems 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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