Optimization of mixture ratio distribution in liquid propellant rocket thrust chamber

Abstract

An optimization problem is set up for determining the propellant mixture ratio distribution in the liquidpropellant rocket thrust chamber that would yield maximum specific impulse. The problem is solved using the method of Lagrangian Multipliers. The results show that uniform mixture ratio distribution in the combustion chamber will give a maximum value of specific impulse for mixture ratios greater than a critical value. Normal operating mixture ratios for liquid-propellant rocket engines are well above this critical value.