Effective Exhaust Velocity of Rocket Calculator

✖Jet Velocity is the effective exhaust velocity.ⓘ Jet Velocity [V_e]			+10% -10%
✖The Nozzle Exit Pressure in rocketry refers to the pressure of the exhaust gases at the exit of the rocket engine nozzle.ⓘ Nozzle Exit Pressure [p₂]			+10% -10%
✖Atmospheric pressure, also known as air pressure or barometric pressure, is the force per unit area exerted by the weight of the Earth's atmosphere above a given point.ⓘ Atmospheric Pressure [p₃]			+10% -10%
✖The Exit Area in rocketry refers to the cross-sectional area at the exit of the rocket engine nozzle, where the exhaust gases are expelled into the surrounding environment.ⓘ Exit Area [A₂]			+10% -10%
✖The Propellant Mass Flow Rate refers to the amount of mass that flows through a given point in the rocket propulsion system per unit time.ⓘ Propellant Mass Flow Rate [ṁ]			+10% -10%

✖Effective exhaust velocity is the velocity of a rocket's exhaust relative to the rocket.ⓘ Effective Exhaust Velocity of Rocket [c]

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Effective Exhaust Velocity of Rocket Solution

STEP 0: Pre-Calculation Summary

Formula Used

Effective Exhaust Velocity = Jet Velocity+(Nozzle Exit Pressure-Atmospheric Pressure)*Exit Area/Propellant Mass Flow Rate
c = V_e+(p₂-p₃)*A₂/ṁ
This formula uses 6 Variables

Variables Used

Effective Exhaust Velocity - (Measured in Meter per Second) - Effective exhaust velocity is the velocity of a rocket's exhaust relative to the rocket.
Jet Velocity - (Measured in Meter per Second) - Jet Velocity is the effective exhaust velocity.
Nozzle Exit Pressure - (Measured in Pascal) - The Nozzle Exit Pressure in rocketry refers to the pressure of the exhaust gases at the exit of the rocket engine nozzle.
Atmospheric Pressure - (Measured in Pascal) - Atmospheric pressure, also known as air pressure or barometric pressure, is the force per unit area exerted by the weight of the Earth's atmosphere above a given point.
Exit Area - (Measured in Square Meter) - The Exit Area in rocketry refers to the cross-sectional area at the exit of the rocket engine nozzle, where the exhaust gases are expelled into the surrounding environment.
Propellant Mass Flow Rate - (Measured in Kilogram per Second) - The Propellant Mass Flow Rate refers to the amount of mass that flows through a given point in the rocket propulsion system per unit time.

STEP 1: Convert Input(s) to Base Unit

Jet Velocity: 118.644 Meter per Second --> 118.644 Meter per Second No Conversion Required
Nozzle Exit Pressure: 1.239 Megapascal --> 1239000 Pascal (Check conversion here)
Atmospheric Pressure: 0.1013 Megapascal --> 101300 Pascal (Check conversion here)
Exit Area: 1.771 Square Meter --> 1.771 Square Meter No Conversion Required
Propellant Mass Flow Rate: 11.32 Kilogram per Second --> 11.32 Kilogram per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

c = V_e+(p₂-p₃)*A₂/ṁ --> 118.644+(1239000-101300)*1.771/11.32

Evaluating ... ...

c = 178110.40195053

STEP 3: Convert Result to Output's Unit

178110.40195053 Meter per Second --> No Conversion Required

FINAL ANSWER

178110.40195053 ≈ 178110.4 Meter per Second <-- Effective Exhaust Velocity

(Calculation completed in 00.011 seconds)

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< Theory Of Rockets Calculators

Rocket Exhaust Gas Velocity

LaTeX 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

LaTeX 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)))

Velocity Increment of Rocket

LaTeX Go Velocity Increment of Rocket = Jet Velocity*ln(Initial Mass of Rocket/Final Mass of Rocket)

Structural Mass Fraction

LaTeX Go Structural Mass Fraction = Structural Mass/(Propellant Mass+Structural Mass)

Effective Exhaust Velocity of Rocket Formula

LaTeX Go

Effective Exhaust Velocity = Jet Velocity+(Nozzle Exit Pressure-Atmospheric Pressure)*Exit Area/Propellant Mass Flow Rate
c = V_e+(p₂-p₃)*A₂/ṁ

What is Exhaust Velocity ?

The exhaust velocity of a rocket, often, refers to the velocity at which the exhaust gases are expelled from the rocket engine nozzle. It represents the speed at which the propellant gases leave the rocket, generating thrust according to Newton's third law of motion: for every action, there is an equal and opposite reaction.

How to Calculate Effective Exhaust Velocity of Rocket?

Effective Exhaust Velocity of Rocket calculator uses Effective Exhaust Velocity = Jet Velocity+(Nozzle Exit Pressure-Atmospheric Pressure)*Exit Area/Propellant Mass Flow Rate to calculate the Effective Exhaust Velocity, The Effective Exhaust Velocity of Rocket is the velocity of an exhaust stream after reduction by effects such as friction, non-axially directed flow, and pressure differences between the inside of the rocket and its surroundings. Effective Exhaust Velocity is denoted by c symbol.

How to calculate Effective Exhaust Velocity of Rocket using this online calculator? To use this online calculator for Effective Exhaust Velocity of Rocket, enter Jet Velocity (V_e), Nozzle Exit Pressure (p₂), Atmospheric Pressure (p₃), Exit Area (A₂) & Propellant Mass Flow Rate (ṁ) and hit the calculate button. Here is how the Effective Exhaust Velocity of Rocket calculation can be explained with given input values -> 177909.4 = 118.644+(1239000-101300)*1.771/11.32.

FAQ

What is Effective Exhaust Velocity of Rocket?

The Effective Exhaust Velocity of Rocket is the velocity of an exhaust stream after reduction by effects such as friction, non-axially directed flow, and pressure differences between the inside of the rocket and its surroundings and is represented as c = V_e+(p₂-p₃)*A₂/ṁ or Effective Exhaust Velocity = Jet Velocity+(Nozzle Exit Pressure-Atmospheric Pressure)*Exit Area/Propellant Mass Flow Rate. Jet Velocity is the effective exhaust velocity, The Nozzle Exit Pressure in rocketry refers to the pressure of the exhaust gases at the exit of the rocket engine nozzle, Atmospheric pressure, also known as air pressure or barometric pressure, is the force per unit area exerted by the weight of the Earth's atmosphere above a given point, The Exit Area in rocketry refers to the cross-sectional area at the exit of the rocket engine nozzle, where the exhaust gases are expelled into the surrounding environment & The Propellant Mass Flow Rate refers to the amount of mass that flows through a given point in the rocket propulsion system per unit time.

How to calculate Effective Exhaust Velocity of Rocket?

The Effective Exhaust Velocity of Rocket is the velocity of an exhaust stream after reduction by effects such as friction, non-axially directed flow, and pressure differences between the inside of the rocket and its surroundings is calculated using Effective Exhaust Velocity = Jet Velocity+(Nozzle Exit Pressure-Atmospheric Pressure)*Exit Area/Propellant Mass Flow Rate. To calculate Effective Exhaust Velocity of Rocket, you need Jet Velocity (V_e), Nozzle Exit Pressure (p₂), Atmospheric Pressure (p₃), Exit Area (A₂) & Propellant Mass Flow Rate (ṁ). With our tool, you need to enter the respective value for Jet Velocity, Nozzle Exit Pressure, Atmospheric Pressure, Exit Area & Propellant Mass Flow Rate 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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