## Fuel Mass Flow rate Solution

STEP 0: Pre-Calculation Summary
Formula Used
Fuel Mass Flow Rate = Propellant Mass Flow Rate/(Propellant Mixture Ratio+1)
f = /(r+1)
This formula uses 3 Variables
Variables Used
Fuel Mass Flow Rate - (Measured in Kilogram per Second) - Fuel Mass Flow Rate The fuel mass flow rate in a rocket engine refers to the rate at which fuel (such as liquid hydrogen, RP-1, or others) is consumed or expelled from the engine.
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.
Propellant Mixture Ratio - Propellant Mixture Ratio defines the ratio of oxidizer mass to fuel mass in a rocket engine's propellant mixture.
STEP 1: Convert Input(s) to Base Unit
Propellant Mass Flow Rate: 11.32 Kilogram per Second --> 11.32 Kilogram per Second No Conversion Required
Propellant Mixture Ratio: 2.4 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
f = ṁ/(r+1) --> 11.32/(2.4+1)
Evaluating ... ...
f = 3.32941176470588
STEP 3: Convert Result to Output's Unit
3.32941176470588 Kilogram per Second --> No Conversion Required
3.32941176470588 3.329412 Kilogram per Second <-- Fuel Mass Flow Rate
(Calculation completed in 00.004 seconds)
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## Credits

Created by LOKESH
Sri Ramakrishna Engineering College (SREC), COIMBATORE
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Verified by Harsh Raj
Indian Institute of Technology, Kharagpur (IIT KGP), West Bengal
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## < 4 Propellents Calculators

Propellant Mass Flow Rate
Propellant Mass Flow Rate = (Nozzle Throat Area*Inlet Nozzle Pressure*Specific Heat Ratio)*sqrt((2/(Specific Heat Ratio+1))^((Specific Heat Ratio+1)/(Specific Heat Ratio-1)))/sqrt(Specific Heat Ratio*[R]*Temperature at Chamber)
Oxidizer Mass Flow Rate
Oxidizer Mass Flow Rate = (Propellant Mixture Ratio*Propellant Mass Flow Rate)/(Propellant Mixture Ratio+1)
Fuel Mass Flow rate
Fuel Mass Flow Rate = Propellant Mass Flow Rate/(Propellant Mixture Ratio+1)
Propellant Mixture Ratio
Propellant Mixture Ratio = Oxidizer Mass Flow Rate/Fuel Mass Flow Rate

## Fuel Mass Flow rate Formula

Fuel Mass Flow Rate = Propellant Mass Flow Rate/(Propellant Mixture Ratio+1)
f = /(r+1)

## What is Fuel ?

Fuel, in the context of rocket propulsion and combustion, refers to a substance or mixture of substances that undergoes chemical reaction with an oxidizer to produce energy in the form of heat and gas. This energy release generates thrust, propelling the rocket forward.

## How to Calculate Fuel Mass Flow rate?

Fuel Mass Flow rate calculator uses Fuel Mass Flow Rate = Propellant Mass Flow Rate/(Propellant Mixture Ratio+1) to calculate the Fuel Mass Flow Rate, The fuel mass flow rate in a rocket engine refers to the rate at which fuel is consumed or expelled from the engine, it is used to determine the flow rate of fuel into the combustion chamber, which in turn affects combustion efficiency, chamber pressure, and thrust generation. Fuel Mass Flow Rate is denoted by f symbol.

How to calculate Fuel Mass Flow rate using this online calculator? To use this online calculator for Fuel Mass Flow rate, enter Propellant Mass Flow Rate (ṁ) & Propellant Mixture Ratio (r) and hit the calculate button. Here is how the Fuel Mass Flow rate calculation can be explained with given input values -> 0.374834 = 11.32/(2.4+1).

### FAQ

What is Fuel Mass Flow rate?
The fuel mass flow rate in a rocket engine refers to the rate at which fuel is consumed or expelled from the engine, it is used to determine the flow rate of fuel into the combustion chamber, which in turn affects combustion efficiency, chamber pressure, and thrust generation and is represented as f = ṁ/(r+1) or Fuel Mass Flow Rate = Propellant Mass Flow Rate/(Propellant Mixture Ratio+1). 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 Mixture Ratio defines the ratio of oxidizer mass to fuel mass in a rocket engine's propellant mixture.
How to calculate Fuel Mass Flow rate?
The fuel mass flow rate in a rocket engine refers to the rate at which fuel is consumed or expelled from the engine, it is used to determine the flow rate of fuel into the combustion chamber, which in turn affects combustion efficiency, chamber pressure, and thrust generation is calculated using Fuel Mass Flow Rate = Propellant Mass Flow Rate/(Propellant Mixture Ratio+1). To calculate Fuel Mass Flow rate, you need Propellant Mass Flow Rate (ṁ) & Propellant Mixture Ratio (r). With our tool, you need to enter the respective value for Propellant Mass Flow Rate & Propellant Mixture 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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