How to Calculate Propellant Mass Flow Rate?
Propellant Mass Flow Rate calculator uses 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) to calculate the Propellant Mass Flow Rate, The Propellant Mass Flow Rate is a crucial parameter that directly influences engine performance and thrust generation. It represents the rate at which mass (propellant) is expelled from the rocket engine, contributing to the generation of thrust. Propellant Mass Flow Rate is denoted by ṁ symbol.
How to calculate Propellant Mass Flow Rate using this online calculator? To use this online calculator for Propellant Mass Flow Rate, enter Nozzle Throat Area (A_{t}), Inlet Nozzle Pressure (P_{1}), Specific Heat Ratio (γ) & Temperature at Chamber (T_{1}) and hit the calculate button. Here is how the Propellant Mass Flow Rate calculation can be explained with given input values -> 11.32815 = (0.21*3700*1.33)*sqrt((2/(1.33+1))^((1.33+1)/(1.33-1)))/sqrt(1.33*[R]*256).