A COMPACT THRUST AUGMENTING EJECTOR EXPERIMENT.
AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO
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The report briefly reviews the potential momentum thrust performance of ejectors. In addition to thrust performance, an ejectors utility to a VSTOL propulsion system is determined by several other factors including ejector size and airducting requirements. A survey of previous ejector experimental results are presented for ejectors with inlet area ratios in the neighborhood of 15 to 20. A compact two-dimensional ejector experiment with an inlet area ratio of 19 is described. This ejector with a 1.9 area ratio exit diffuser achieved a thrust augmentation ratio of 1.71 and 1.78 for an ejector length to minimum channel width ratio of 3.5 and 5.1 respectively. It is believed that improvements in primary injection techniques were responsible for this favorable thrust performance. Author
- Fluid Mechanics