## Tsiolkovsky Rocket Equation Solution

STEP 0: Pre-Calculation Summary
Formula Used
Change in Rocket Velocity = Specific Impulse*[g]*ln(Wet Mass/Dry mass)
ΔV = Isp*[g]*ln(Mwet/Mdry)
This formula uses 1 Constants, 1 Functions, 4 Variables
Constants Used
[g] - Gravitational acceleration on Earth Value Taken As 9.80665 Meter/Second²
Functions Used
ln - Natural logarithm function (base e), ln(Number)
Variables Used
Change in Rocket Velocity - (Measured in Meter per Second) - Change in rocket velocity is the difference between the initial velocity of the rocket to its final state velocity.
Specific Impulse - (Measured in Second) - Specific Impulse may be defined as the ratio of the thrust produced to the weight flow of the propellants in case solid propellant rocket motors.
Wet Mass - (Measured in Kilogram) - Wet Mass is the mass of a rocket including its contents and propellant.
Dry mass - (Measured in Kilogram) - Dry mass is the mass of the rocket at full ascent.
STEP 1: Convert Input(s) to Base Unit
Specific Impulse: 10 Second --> 10 Second No Conversion Required
Wet Mass: 30000 Kilogram --> 30000 Kilogram No Conversion Required
Dry mass: 25000 Kilogram --> 25000 Kilogram No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
ΔV = Isp*[g]*ln(Mwet/Mdry) --> 10*[g]*ln(30000/25000)
Evaluating ... ...
ΔV = 17.8796369493343
STEP 3: Convert Result to Output's Unit
17.8796369493343 Meter per Second --> No Conversion Required
17.8796369493343 17.87964 Meter per Second <-- Change in Rocket Velocity
(Calculation completed in 00.004 seconds)
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## Credits

Created by Kaki Varun Krishna
Mahatma Gandhi Institute of Technology (MGIT), Hyderabad
Kaki Varun Krishna has created this Calculator and 25+ more calculators!
Verified by Akshay
Maniapal University (MUJ), Jaipur
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## < 15 Rocket Propulsion Calculators

Mass Flow Rate through Engine
Mass Flowrate = Mach Number*Area*Total Pressure*sqrt(Specific Heat Ratio Dynamic/(Total Temperature*Universal Gas Constant))*(1+(Specific Heat Ratio Dynamic-1)* Mach Number^2/2)^(-(Specific Heat Ratio Dynamic+1)/(2*Specific Heat Ratio Dynamic-2))
Compressible Area Ratio
Area Ratio = ((Specific Heat Ratio Dynamic+1)/2)^(-(Specific Heat Ratio Dynamic+1)/(2*Specific Heat Ratio Dynamic-2))*((1+(Specific Heat Ratio Dynamic-1)*Mach Number^2/2)^((Specific Heat Ratio Dynamic+1)/(2*Specific Heat Ratio Dynamic-2)))/Mach Number
Exit Velocity given Molar Mass
Exit Velocity = sqrt(((2*Inlet Temperature*Universal Gas Constant*Specific Heat Ratio Dynamic)/(Molar Mass)/(Specific Heat Ratio Dynamic-1))*(1-(Exit Pressure/Inlet Pressure)^(1-1/Specific Heat Ratio Dynamic)))
Exit Velocity given Specific Heat Capacity
Exit Velocity = sqrt(2*Total Temperature*Molar Specific Heat Capacity at Constant Pressure*(1-(Exit Pressure/Inlet Pressure)^(1-1/Specific Heat Ratio Dynamic)))
Exit Pressure
Exit Pressure = Inlet Pressure*(((1+(Specific Heat Ratio Dynamic-1)/2*Mach Number^2))^-((Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic-1)))
Exit Velocity given Mach Number and Exit Temperature
Exit Velocity = Mach Number*sqrt(Specific Heat Ratio*Universal Gas Constant*Exit Temperature)
Tsiolkovsky Rocket Equation
Change in Rocket Velocity = Specific Impulse*[g]*ln(Wet Mass/Dry mass)
Exit Temperature
Exit Temperature = Total Temperature*(1+(Specific Heat Ratio Dynamic-1)/2*Mach Number^2)^-1
Power required to produce Exhaust Jet Velocity given Mass of Rocket and Acceleration
Power Required = (Mass of Rocket*Acceleration*Rocket Exhaust Velocity)/2
Rocket Mass Ratio
Rocket Mass Ratio = e^(Change in Rocket Velocity/Rocket Exhaust Velocity)
Thrust given Exhaust Velocity and Mass Flow Rate
Thrust at Crown or Abutments = Air Flow Rate*Jet Velocity of Aircraft
Photon Propulsion Thrust
Thrust at Crown or Abutments = 1000*Power in Jet/Velocity of Light
Power required to produce Exhaust Jet Velocity
Power Required = 1/2*Air Flow Rate*Jet Velocity of Aircraft^2
Thrust given Mass and Acceleration of Rocket
Thrust at Crown or Abutments = Mass*Acceleration
Acceleration of Rocket
Acceleration = Thrust at Crown or Abutments/Mass

## < 10+ Parameters Calculators

Helicopter Flying Range
Range of Aircraft = 270*Weight of Fuel/Aircraft Weight *Lift Coefficient/Drag Coefficient*Rotor efficiency*(Coefficient of Power loss)/Specific Fuel Consumption
Depth of Missile Penetration into Concrete Element of Infinite Thickness (meters)
Missile depth of penetration = 12*Penetration Coefficient Concrete*Missile Wt./Frontal area of missile*log10(1+Missile striking velocity^2/215000)
Weight of Glider
Weight Of Glider = Lift Force*cos(Glide Angle)+Drag Force*sin(Glide Angle)
Orbital Period
Orbital period = 2*pi*sqrt((Radius of Orbit^3)/([G.]*Central body Mass))
Tsiolkovsky Rocket Equation
Change in Rocket Velocity = Specific Impulse*[g]*ln(Wet Mass/Dry mass)
Modern Lift Equation
Lift on Airfoil = (Lift Coefficient* Air Density* Aircraft Gross Wing Area* Fluid Velocity)/2
Load = Aircraft Weight/((pi*Diameter of Rotor)/4)
Rocket Mass Ratio
Rocket Mass Ratio = e^(Change in Rocket Velocity/Rocket Exhaust Velocity)
Blade lift coefficient = 6*Thrust Coefficient/Rotor Solidity

## Tsiolkovsky Rocket Equation Formula

Change in Rocket Velocity = Specific Impulse*[g]*ln(Wet Mass/Dry mass)
ΔV = Isp*[g]*ln(Mwet/Mdry)

## What is the rocket equation used for?

Once the initial and final masses and the exhaust velocity of the vehicle are known, the rocket equation can be used to calculate the total change in velocity

## How to Calculate Tsiolkovsky Rocket Equation?

Tsiolkovsky Rocket Equation calculator uses Change in Rocket Velocity = Specific Impulse*[g]*ln(Wet Mass/Dry mass) to calculate the Change in Rocket Velocity, The Tsiolkovsky Rocket Equation, also called classical rocket equation, or ideal rocket equation is a mathematical equation that describes the motion of vehicles that follow the basic principle of a rocket. Change in Rocket Velocity is denoted by ΔV symbol.

How to calculate Tsiolkovsky Rocket Equation using this online calculator? To use this online calculator for Tsiolkovsky Rocket Equation, enter Specific Impulse (Isp), Wet Mass (Mwet) & Dry mass (Mdry) and hit the calculate button. Here is how the Tsiolkovsky Rocket Equation calculation can be explained with given input values -> 17.87964 = 10*[g]*ln(30000/25000).

### FAQ

What is Tsiolkovsky Rocket Equation?
The Tsiolkovsky Rocket Equation, also called classical rocket equation, or ideal rocket equation is a mathematical equation that describes the motion of vehicles that follow the basic principle of a rocket and is represented as ΔV = Isp*[g]*ln(Mwet/Mdry) or Change in Rocket Velocity = Specific Impulse*[g]*ln(Wet Mass/Dry mass). Specific Impulse may be defined as the ratio of the thrust produced to the weight flow of the propellants in case solid propellant rocket motors, Wet Mass is the mass of a rocket including its contents and propellant & Dry mass is the mass of the rocket at full ascent.
How to calculate Tsiolkovsky Rocket Equation?
The Tsiolkovsky Rocket Equation, also called classical rocket equation, or ideal rocket equation is a mathematical equation that describes the motion of vehicles that follow the basic principle of a rocket is calculated using Change in Rocket Velocity = Specific Impulse*[g]*ln(Wet Mass/Dry mass). To calculate Tsiolkovsky Rocket Equation, you need Specific Impulse (Isp), Wet Mass (Mwet) & Dry mass (Mdry). With our tool, you need to enter the respective value for Specific Impulse, Wet Mass & Dry mass and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well. Let Others Know