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An investigation of corner separation within a thrust augmenter having Coanda jetsThe development of separation in corners of thrust augmentor wings having Coanda jets was investigated using hot film surface sensors and pressure transducers. Separation on the test augmentor began at a corner very close to the augmentor exit and then rapidly proceeded upstream. Measurements of the pressure fields in the corner region indicated that a modified form of the Stratford criterion could be used to predict the onset of separation. Testing was conducted over a range of nozzle pressure ratios, aspect ratios, diffuser angles, and designs of the boundary layer and Coanda nozzles.
Document ID
19800001883
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Seiler, M. R. (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
Report/Patent Number
NADC-76153-30
Accession Number
80N10122
Funding Number(s)
CONTRACT_GRANT: N62269-76-C-0402
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19800001868Collected WorksWorkshop on Thrust Augmenting Ejectors
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