Accession Number:

ADA142650

Title:

Thrust Augmentation Study of High Performance Ejectors.

Descriptive Note:

Final rept. 15 Mar 82-15 Mar 83,

Corporate Author:

DAYTON UNIV OH RESEARCH INST

Personal Author(s):

Report Date:

1983-11-01

Pagination or Media Count:

88.0

Abstract:

A technique is developed for determining a representative value of the maximum efficiency that can be achieved with high performance ejectors when operating on the supersonic solution branch of an ejector. These efficiencies are used to calculate thrust augmentation for an ejector over a wide range of parameters including operation with a hypothetical engine. Reasonable values of thrust augmentation can be achieved at low subsonic flight mach numbers. However, at flight Mach numbers near one, little or not thrust augmentation was found. At supersonic flight Mach numbers, thrust augmentation was achieved. Basic studies indicated that the effects of temperature was opposite at subsonic and supersonic flight Mach numbers. Thrust augmentation decreased with increasing temperature at subsonic Mach number sand increased with increasing temperature at supersonic Mach numbers.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE