Accession Number:

AD0617621

Title:

ANALYSIS OF THRUST AND FLOW AUGMENTATION OF A COANDA NOZZLE.

Descriptive Note:

Final rept.,

Corporate Author:

HUYCK RESEARCH CENTER STAMFORD CONN

Personal Author(s):

Report Date:

1965-05-01

Pagination or Media Count:

62.0

Abstract:

In order to evaluate the performance of a Coanda Nozzle and to determine its thrust and pumping capabilities, a series of tests were conducted on a Coanda Nozzle. The results showed that the nozzle was capable of creating thrust augmentation of about 1.25. Furthermore, it was also shown that the Coanda Nozzle, through the creation of a low pressure zone along the Coanda surface, was capable of augmenting the momentum of the primary by a factor of approximately 1.7. By measuring the velocity profile at the exit of the nozzle, the pumping capability of the nozzle as defined by the flow augmentation ratio was calculated and determined to be inversely proportional to the slot size, while reaching a maximum at plenum pressures ranging from 150 to 180 cm. Hg. Based on the experiments carried out on other nozzles, it has been shown that the momentum and flow augmentation reach their greatest value for slot sizes smaller than possible with the nozzle furnished by the Air Force. The results confirmed the conclusion that this particular configuration of the Coanda nozzle is not optimum for purposes of producing high static thrust. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE