Supersonic Combustion Chemistry and Mixing of High Energy Density Fuels Related to Advanced Air-Breathing Engine Design.

摘要

The program is directed towards answering the following question. Given a boron combustible particle of known initial size and composition moving at a high relative velocity in a gaseous medium,how are the combustion behavior and particle dynamics influenced by the particle (gas relative velocity,gas composition,temperature,and pressure anticipated in operational combustors. The role of the shock tube in answering this question is discussed. An 'ideal'experiment is postulated and several possible practical experimental techniques are assessed relative to this standard. To aid in the assessment of the practicality of an experimental technique, a computer program was developed to compute particle trajectories for shock tube flows. Some preliminary experiments aimed at establishing the applicability of a reflected shock technique to the measurement of burning particle drag coefficients were carried out. The results of these experiments yielded very high values of the drag coefficient. At the present time,it is not known if this result was due to the roughness of the particles,static charge effects,the effect of combustion or the preliminary nature of the experiments. In all probability a combination of the above factors is involved. (Author)