Dual Cavity Scramjet Operability and Performance Study (Postprint)

摘要

The purpose of this study is to compare the operability and performance of a dual cavity supersonic combustor with that of a single cavity over various flight conditions, equivalence ratios, and fuel injection schemes. Experimental and numerical approaches will be used to explore the effects of various fueling schemes for both single and dual cavities. Discrete flight conditions from Mach 3.5 to 5.0 at flight dynamic pressures from approximately 500 to 2000 psf were studied. The objectives of this study include: 1) investigate the effects of adding a second cavity to a scramjet flow path, and 2) determine and analyze the performance and operability of the dual cavity for various conditions. Measurements including streamwise pressure distribution profiles, peak and exit pressure ratios, and stream thrust have been obtained. Results suggest a significant increase in performance using a dual cavity flame holder.