Combustion Properties of High-Density Fuels

The present investigation has been undertaken with the aim of developing a technique to investigate the combustion of fuel mist in a simulated rocket engine environment. The approach taken consists of the development of the nebulizer-coupled-shock-tube technique and its application to the proposed ASALM fuel, RJ-5. The method involves using shock induced heating to initiate combustion of fuel air mist in the reflected shock zone and monitoring the burning process using various spectroscopic techniques. The construction details as well as a number of important experimental considerations have previously been discussed. The project is proceeding on schedule. The entire system is operational and combustion of RJ-5 mist has been observed. (Author)