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Design and test of a prototype scale ejector wingA two dimensional momentum integral analysis was used to examine the effect of changing inlet area ratio, diffuser area ratio, and the ratio of ejector length to width. A relatively wide range of these parameters was considered. It was found that for constant inlet area ratio the augmentation increases with the ejector length, and for constant length: width ratio the augmentation increases with inlet area ratio. Scale model tests were used to verify these trends and to examine th effect of aspect ratio. On the basis of these results, an ejector configuration was selected for fabrication and testing at a scale representative of an ejector wing aircraft. The test ejector was powered by a Pratt-Whitney F401 engine developing approximately 12,000 pounds of thrust. The results of preliminary tests indicate that the ejector develops a thrust augmentation ratio better than 1.65.
Document ID
19800001892
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mefferd, L. A. (Rockwell International Corp. Columbus, OH, United States)
Alden, R. E. (Rockwell International Corp. Columbus, OH, United States)
Bevilacqua, P. M. (Rockwell International Corp. Columbus, OH, United States)
Date Acquired
August 10, 2013
Publication Date
September 1, 1979
Publication Information
Publication: NASA. Ames Res. Center Workshop on Thrust Augmenting Ejectors
Subject Category
Aerodynamics
Accession Number
80N10131
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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