Characteristics Velocity 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%

✖Characteristics Velocity is a measure of the effectiveness with which the combustion in a rocket engine produces high temperature and pressure.ⓘ Characteristics Velocity [C^✸]

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Characteristics Velocity Solution

STEP 0: Pre-Calculation Summary

Formula Used

Characteristics Velocity = sqrt((([R]*Temperature at Chamber)/Specific Heat Ratio)*((Specific Heat Ratio+1)/2)^((Specific Heat Ratio+1)/(Specific Heat Ratio-1)))
C^✸ = sqrt((([R]*T₁)/γ)*((γ+1)/2)^((γ+1)/(γ-1)))
This formula uses 1 Constants, 1 Functions, 3 Variables

Constants Used

[R] - Universal gas constant Value Taken As 8.31446261815324

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Characteristics Velocity - (Measured in Meter per Second) - Characteristics Velocity is a measure of the effectiveness with which the combustion in a rocket engine produces high temperature and pressure.
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

C^✸ = sqrt((([R]*T₁)/γ)*((γ+1)/2)^((γ+1)/(γ-1))) --> sqrt((([R]*256)/1.33)*((1.33+1)/2)^((1.33+1)/(1.33-1)))

Evaluating ... ...

C^✸ = 68.5901685380425

STEP 3: Convert Result to Output's Unit

68.5901685380425 Meter per Second --> No Conversion Required

FINAL ANSWER

68.5901685380425 ≈ 68.59017 Meter per Second <-- Characteristics Velocity

(Calculation completed in 00.004 seconds)

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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

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< 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)

Characteristics Velocity Formula

LaTeX Go

What is Characteristics Velocity?

Characteristic velocity is a crucial parameter in rocket propulsion. It's also known as specific impulse and is typically measured in seconds (s). This parameter represents the efficiency of a rocket engine. Specifically, it measures how effectively the rocket can convert its propellant mass into thrust.

How to Calculate Characteristics Velocity?

Characteristics Velocity calculator uses Characteristics Velocity = sqrt((([R]*Temperature at Chamber)/Specific Heat Ratio)*((Specific Heat Ratio+1)/2)^((Specific Heat Ratio+1)/(Specific Heat Ratio-1))) to calculate the Characteristics Velocity, Characteristics Velocity formula is defined as a measure of the speed at which a rocket can effectively utilize its propellant, reflecting the relationship between thrust, temperature, and specific heat ratio in rocket propulsion systems. Characteristics Velocity is denoted by C^✸ symbol.

How to calculate Characteristics Velocity using this online calculator? To use this online calculator for Characteristics Velocity, enter Temperature at Chamber (T₁) & Specific Heat Ratio (γ) and hit the calculate button. Here is how the Characteristics Velocity calculation can be explained with given input values -> 68.59017 = sqrt((([R]*256)/1.33)*((1.33+1)/2)^((1.33+1)/(1.33-1))).

FAQ

What is Characteristics Velocity?

Characteristics Velocity formula is defined as a measure of the speed at which a rocket can effectively utilize its propellant, reflecting the relationship between thrust, temperature, and specific heat ratio in rocket propulsion systems and is represented as C^✸ = sqrt((([R]*T₁)/γ)*((γ+1)/2)^((γ+1)/(γ-1))) or Characteristics Velocity = sqrt((([R]*Temperature at Chamber)/Specific Heat Ratio)*((Specific Heat Ratio+1)/2)^((Specific Heat Ratio+1)/(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 Characteristics Velocity?

Characteristics Velocity formula is defined as a measure of the speed at which a rocket can effectively utilize its propellant, reflecting the relationship between thrust, temperature, and specific heat ratio in rocket propulsion systems is calculated using Characteristics Velocity = sqrt((([R]*Temperature at Chamber)/Specific Heat Ratio)*((Specific Heat Ratio+1)/2)^((Specific Heat Ratio+1)/(Specific Heat Ratio-1))). To calculate Characteristics Velocity, 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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