Performance of a Titan rocket engine using laser-induced fluorescence of OH

Abstract

Rocket engine performance can be modeled by considering separately the propellant delivery system distribution, combustion efficiency including propellant vaporization and gas-phase mixing, and nozzle expansion efficiency. Although these quantities can be modeled, experimental verification is extremely helpful for separately understanding these processes and for design improvements. Laser-induced fluorescence of OH, excited by a KrF excimer laser operating at 248 nm, is used to measure the concentration of the OH radical across the exit plane of a firing Titan IV, stage I, liquid rocket engine, from which the combusting mixture ratio profile could be inferred