Throat Velocity of Nozzle Solution

STEP 0: Pre-Calculation Summary
Formula Used
Throat Velocity = sqrt((2*Specific Heat Ratio)/(Specific Heat Ratio+1)*[R]*Temperature at Chamber)
vt = sqrt((2*γ)/(γ+1)*[R]*T1)
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
Throat Velocity - (Measured in Meter per Second) - The throat velocity in rocketry refers to the velocity of the gases passing through the throat of the rocket engine nozzle.
Specific Heat Ratio - The specific heat ratio describes the ratio of specific heats of a gas at constant pressure to that at constant volume.
Temperature at Chamber - (Measured in Kelvin) - Temperature at Chamber typically refers to the temperature inside a closed chamber or enclosure.
STEP 1: Convert Input(s) to Base Unit
Specific Heat Ratio: 1.33 --> No Conversion Required
Temperature at Chamber: 256 Kelvin --> 256 Kelvin No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
vt = sqrt((2*γ)/(γ+1)*[R]*T1) --> sqrt((2*1.33)/(1.33+1)*[R]*256)
Evaluating ... ...
vt = 49.2946665252529
STEP 3: Convert Result to Output's Unit
49.2946665252529 Meter per Second --> No Conversion Required
FINAL ANSWER
49.2946665252529 49.29467 Meter per Second <-- Throat Velocity
(Calculation completed in 00.006 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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9 Theory Of Rockets Calculators

Rocket Exhaust Gas Velocity
​ Go Jet Velocity = sqrt(((2*Specific Heat Ratio)/(Specific Heat Ratio-1))*[R]*Temperature at Chamber*(1-(Nozzle Exit Pressure/Pressure at Chamber)^((Specific Heat Ratio-1)/Specific Heat Ratio)))
Total Velocity Required to Place Satellite in Orbit
​ Go Total Velocity of Rocket = sqrt(([G.]*Mass Of Earth*(Radius of Earth+2*Height of Satellite))/(Radius of Earth*(Radius of Earth+Height of Satellite)))
Effective Exhaust Velocity of Rocket
​ Go Effective Exhaust Velocity = Jet Velocity+(Nozzle Exit Pressure-Atmospheric Pressure)*Exit Area/Propellant Mass Flow Rate
Throat Velocity of Nozzle
​ Go Throat Velocity = sqrt((2*Specific Heat Ratio)/(Specific Heat Ratio+1)*[R]*Temperature at Chamber)
Velocity Increment of Rocket
​ Go Velocity Increment of Rocket = Jet Velocity of Rocket*ln(Initial Mass of Rocket/Final Mass of Rocket)
Structural Mass Fraction
​ Go Structural Mass Fraction = Structural Mass/(Propellant Mass+Structural Mass)
Payload Mass Fraction
​ Go Payload Mass Fraction = Payload Mass/(Propellant Mass+Structural Mass)
Propellent Mass Fraction
​ Go Propellant Mass Fraction = Propellant Mass/Initial Mass
Mass Ratio of Rocket
​ Go Mass Ratio = Final Mass/Initial Mass

Throat Velocity of Nozzle Formula

Throat Velocity = sqrt((2*Specific Heat Ratio)/(Specific Heat Ratio+1)*[R]*Temperature at Chamber)
vt = sqrt((2*γ)/(γ+1)*[R]*T1)

What is Throat Velocity ?

The throat velocity in rocketry refers to the velocity of the gases passing through the throat of the rocket engine nozzle, the throat is the narrowest section of the nozzle where the flow area is minimized to achieve the highest possible gas velocity at that point, it is a crucial parameter in rocket engine design as it determines the maximum velocity of the exhaust gases at the throat, this velocity is typically much higher than the velocity of the rocket itself.

How to Calculate Throat Velocity of Nozzle?

Throat Velocity of Nozzle calculator uses Throat Velocity = sqrt((2*Specific Heat Ratio)/(Specific Heat Ratio+1)*[R]*Temperature at Chamber) to calculate the Throat Velocity, The Throat Velocity of Nozzle refers to the velocity of the exhaust gases as they pass through the narrowest section of the rocket engine nozzle, it is a crucial parameter in rocket engine design as it determines the maximum velocity of the exhaust gases at the throat. Throat Velocity is denoted by vt symbol.

How to calculate Throat Velocity of Nozzle using this online calculator? To use this online calculator for Throat Velocity of Nozzle, enter Specific Heat Ratio (γ) & Temperature at Chamber (T1) and hit the calculate button. Here is how the Throat Velocity of Nozzle calculation can be explained with given input values -> 49.29467 = sqrt((2*1.33)/(1.33+1)*[R]*256).

FAQ

What is Throat Velocity of Nozzle?
The Throat Velocity of Nozzle refers to the velocity of the exhaust gases as they pass through the narrowest section of the rocket engine nozzle, it is a crucial parameter in rocket engine design as it determines the maximum velocity of the exhaust gases at the throat and is represented as vt = sqrt((2*γ)/(γ+1)*[R]*T1) or Throat Velocity = sqrt((2*Specific Heat Ratio)/(Specific Heat Ratio+1)*[R]*Temperature at Chamber). The specific heat ratio describes the ratio of specific heats of a gas at constant pressure to that at constant volume & Temperature at Chamber typically refers to the temperature inside a closed chamber or enclosure.
How to calculate Throat Velocity of Nozzle?
The Throat Velocity of Nozzle refers to the velocity of the exhaust gases as they pass through the narrowest section of the rocket engine nozzle, it is a crucial parameter in rocket engine design as it determines the maximum velocity of the exhaust gases at the throat is calculated using Throat Velocity = sqrt((2*Specific Heat Ratio)/(Specific Heat Ratio+1)*[R]*Temperature at Chamber). To calculate Throat Velocity of Nozzle, you need Specific Heat Ratio (γ) & Temperature at Chamber (T1). With our tool, you need to enter the respective value for Specific Heat Ratio & Temperature at Chamber 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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