Performance characteristics of aircraft cooling ejectors having short cylindrical shrouds

Fred D. Kochendorfer, Morris D. Rousso
May 1951

The factors affecting the performance of ejector suitable for aircraft cooling are investigated theoretically and experimentally. The investigation covers a range of shroud- to-nozzle diameter ratios from 1.1 to 1.6, of shroud lengths from 0.2 to 2.28 nozzle diameters, of secondary-to-primary weight-flow ratios from 0 to 0.12, and of ambient- to-nozzle pressure ratios from 0.7 to 0.06. The results of a simplified theoretical analysis based on each type of flow are in good agreement with those experimentally obtained.

An Adobe Acrobat (PDF) file of the entire report: