Accession Number:

ADP000529

Title:

Ejector Nozzle Development

Descriptive Note:

Corporate Author:

ROCKWELL INTERNATIONAL COLUMBUS OH NORTH AMERICAN AIRCRAFT OPERATIONS

Personal Author(s):

Report Date:

1982-06-01

Pagination or Media Count:

25.0

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.

Subject Categories:

  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE