Accession Number:

ADA125529

Title:

Experimental Investigation of High Performance, Short, Thrust Augmenting Ejectors

Descriptive Note:

Final rept.

Corporate Author:

CLEMSON UNIV SC DEPT OF MECHANICAL ENGINEERING

Report Date:

1983-01-01

Pagination or Media Count:

69.0

Abstract:

Results of an experimental investigation concerning the design and testing of air-to-air thrust augmenting ejectors utilizing short curved-wall diffusers are presented. These ejectors were designed primarily according to the procedure established in an analytical research effort sponsored by DTNSRDC from 1980-1981. Two of the three ejectors tested have identical mixing chambers. The mixing chamber inlet area to the primary nozzle area ratio lambda was 40. The overall ejector length-to-mixing chamber diameter ratios LDoverall were 6.09 and 6.16 diffuser area ratios ARdiff were 1.33 and 1.46, respectively. The third ejector had an LDoverall of 6.02, a lambda of 20 and an ARdiff of 1. 26. The best observed thrust augmentation ratio phi and the modified thrust augmentation ratio phi sub 2 were 2.11 and 1.91 respectively for a sonic primary jet. The modified thrust augmentation ratio phi sub 2 accounts for the penalty of suction in preventing flow separation in the diffuser. These levels of thrust ratio were derived from velocity measurements at the ejector exit. Independent thrust measurements obtained with strain gages on the mixing chamber agree with the force calculated from the momentum data. The experimentally observed ejector performance data correlated well with the predicted values. Author

Subject Categories:

  • Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE