PERFORMANCE INVESTIGATION OF A NONPUMPING ROCKET EJECTOR SYSTEM FOR ALTITUDE SIMULATION

摘要

The effect of various dimensions on the performance of a prototype, no pumping cylindrical-rocket-ejector system was studied both theoretically and experimental] y. The rocket-ejector system contained a convergent-divergent nozzle with a nozzle exit-to-throat area ratio of 9. Various length and diameter ejector tubes enclosed the nozzle;Highpressure nitrogen gas flowed through the nozzle and served as the pumping fluid.nThe cross-sectional area ratio of ejector tube to nozzle throat and the ratio of ejector-tube length to diameter were investigated. A range of ejector-tube area ratios from 16 to 49 and ejector-tube length-to diameter ratios from 2.67 to 12.0 was studied for various ratios of pumping pressure to atmospheric pressure. The range for the pumping pressure ratios was from 3 to 44.