Ejector Nozzle Development
Abstract
A combination of computer analysis and scale model testing was utilized to develop a nozzle which would increase the performance of thrust augmenting ejectors. Scale model tests were conducted on various multi-lobed and vortex generating nozzles. Predicted jet characteristics were obtained by calculating a finite difference solution of Reynolds equations for the three- dimensional flow field. A two-equation turbulence kinetic energy model was used for closure. It is demonstrated that the thrust augmentation of the XFV-12A ejector can be increased from 1.45 to 1.64 by the addition of lobes to the baseline nozzle, and a corresponding increase of throat width.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1982
- Accession Number
- ADP000529
Entities
People
- E. J. Schum
- J. H. Dehart