## Propellant Mixture Ratio Solution

STEP 0: Pre-Calculation Summary
Formula Used
Propellant Mixture Ratio = Oxidizer Mass Flow Rate/Fuel Mass Flow Rate
r = o/f
This formula uses 3 Variables
Variables Used
Propellant Mixture Ratio - Propellant Mixture Ratio defines the ratio of oxidizer mass to fuel mass in a rocket engine's propellant mixture.
Oxidizer Mass Flow Rate - (Measured in Kilogram per Second) - The oxidizer mass flow rate in a rocket engine refers to the rate at which oxidizer (such as liquid oxygen) is consumed or expelled from the engine.
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.
STEP 1: Convert Input(s) to Base Unit
Oxidizer Mass Flow Rate: 10 Kilogram per Second --> 10 Kilogram per Second No Conversion Required
Fuel Mass Flow Rate: 4.1 Kilogram per Second --> 4.1 Kilogram per Second No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
r = ṁo/ṁf --> 10/4.1
Evaluating ... ...
r = 2.4390243902439
STEP 3: Convert Result to Output's Unit
2.4390243902439 --> No Conversion Required
2.4390243902439 2.439024 <-- Propellant Mixture Ratio
(Calculation completed in 00.004 seconds)
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## Credits

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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## < 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

## Propellant Mixture Ratio Formula

Propellant Mixture Ratio = Oxidizer Mass Flow Rate/Fuel Mass Flow Rate
r = o/f

## What is Propellant Mixture ?

The propellant mixture, in the context of rocket propulsion, refers to the combination of oxidizer and fuel used to generate thrust in a rocket engine. Propellant mixtures are carefully formulated to provide the necessary chemical reactions and energy release required for propulsion.

## How to Calculate Propellant Mixture Ratio?

Propellant Mixture Ratio calculator uses Propellant Mixture Ratio = Oxidizer Mass Flow Rate/Fuel Mass Flow Rate to calculate the Propellant Mixture Ratio, The propellant mixture ratio is a fundamental parameter that represents the ratio of the oxidizer mass flow rate to the fuel mass flow rate in a rocket engine's propellant mixture, it directly affects combustion efficiency, specific impulse, thrust, and other performance parameters. Propellant Mixture Ratio is denoted by r symbol.

How to calculate Propellant Mixture Ratio using this online calculator? To use this online calculator for Propellant Mixture Ratio, enter Oxidizer Mass Flow Rate (ṁo) & Fuel Mass Flow Rate (ṁf) and hit the calculate button. Here is how the Propellant Mixture Ratio calculation can be explained with given input values -> 2.439024 = 10/4.1.

### FAQ

What is Propellant Mixture Ratio?
The propellant mixture ratio is a fundamental parameter that represents the ratio of the oxidizer mass flow rate to the fuel mass flow rate in a rocket engine's propellant mixture, it directly affects combustion efficiency, specific impulse, thrust, and other performance parameters and is represented as r = ṁo/ṁf or Propellant Mixture Ratio = Oxidizer Mass Flow Rate/Fuel Mass Flow Rate. The oxidizer mass flow rate in a rocket engine refers to the rate at which oxidizer (such as liquid oxygen) is consumed or expelled from the engine & 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.
How to calculate Propellant Mixture Ratio?
The propellant mixture ratio is a fundamental parameter that represents the ratio of the oxidizer mass flow rate to the fuel mass flow rate in a rocket engine's propellant mixture, it directly affects combustion efficiency, specific impulse, thrust, and other performance parameters is calculated using Propellant Mixture Ratio = Oxidizer Mass Flow Rate/Fuel Mass Flow Rate. To calculate Propellant Mixture Ratio, you need Oxidizer Mass Flow Rate (ṁo) & Fuel Mass Flow Rate (ṁf). With our tool, you need to enter the respective value for Oxidizer Mass Flow Rate & Fuel 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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