Propellant Mixture Ratio Calculator

✖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.ⓘ Oxidizer Mass Flow Rate [ṁ_o]			+10% -10%
✖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.ⓘ Fuel Mass Flow Rate [ṁ_f]			+10% -10%

✖Propellant Mixture Ratio defines the ratio of oxidizer mass to fuel mass in a rocket engine's propellant mixture.ⓘ Propellant Mixture Ratio [r]

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Propellant Mixture Ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

Propellant Mixture Ratio = Oxidizer Mass Flow Rate/Fuel Mass Flow Rate
r = ṁ_o/ṁ_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 = ṁ_o/ṁ_f --> 10/4.1

Evaluating ... ...

r = 2.4390243902439

STEP 3: Convert Result to Output's Unit

2.4390243902439 --> No Conversion Required

FINAL ANSWER

2.4390243902439 ≈ 2.439024 <-- Propellant Mixture Ratio

(Calculation completed in 00.004 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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< Propellents Calculators

Propellant Mass Flow Rate

LaTeX Go 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

LaTeX Go Oxidizer Mass Flow Rate = (Propellant Mixture Ratio*Propellant Mass Flow Rate)/(Propellant Mixture Ratio+1)

Fuel Mass Flow rate

LaTeX Go Fuel Mass Flow Rate = Propellant Mass Flow Rate/(Propellant Mixture Ratio+1)

Propellant Mixture Ratio

LaTeX Go Propellant Mixture Ratio = Oxidizer Mass Flow Rate/Fuel Mass Flow Rate

Propellant Mixture Ratio Formula

LaTeX Go

Propellant Mixture Ratio = Oxidizer Mass Flow Rate/Fuel Mass Flow Rate
r = ṁ_o/ṁ_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 (ṁ_o) & Fuel Mass Flow Rate (ṁ_f) 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 = ṁ_o/ṁ_f 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 (ṁ_o) & Fuel Mass Flow Rate (ṁ_f). 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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