Supersonic Combustion Experiments with a Cavity-Based Fuel Injector

Recent results from combustion experimentsin a direct-connectsupersoniccombustorarepresented. Successful ignition and sustained combustion of gaseous ethylene have been achieved using an injector/e ameholder concept with low-angle, e ush-wall fuel injection upstream of a wall cavity. Two interchangeable facility nozzles (Mach 1.8 and 2.2) were used to obtain combustor inlet e ow properties that simulate e ight conditions between Mach 4 and 6 at a dynamic pressure of 47.9 kPa. Mainstream combustion was achieved at equivalence ratios between 0.25 and 0.75 using only a spark plug and no other external ignition aids. Delta-force levels between 667 and 1779 N were measured, with corresponding combustor pressure ratios between 3.1 and 4.0. Video records of the e ame zone show an intensely active combustion zone with rapid e ame spreading. One-dimensional performance analysis of the test data indicates a combustion efe ciency around 80% with an average combustor skin friction coefe cient of 0.0028.