STUDY OF THE THRUST PRODUCED BY A COANDA NOZZLE.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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An experimental study was performed to determine the influence of geometry on the thrust of a two-dimensional Coanda-effect nozzle and to determine the fluid flow rate required to switch the primary fluid jet by injection parallel to nozzle axis. The thrust varied from 3 to 40 Lbf as nozzle pressure ratio varied from 1.3 to 5.3 for nozzle divergence half-angles from 10 degrees to 20 degrees and ratio of diverging wall spacing at the throat to throat width db from 3 to 8. Author
- Fluidics and Fluerics