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A study on vortex flow control of inlet distortion in the re-engined 727-100 center inlet duct using computational fluid dynamicsComputational fluid dynamics was used to investigate the management of inlet distortion by the introduction of discrete vorticity sources at selected locations in the inlet for the purpose of controlling secondary flow. These sources of vorticity were introduced by means of vortex generators. A series of design observations were made concerning the importance of various vortex generator design parameters in minimizing engine face circumferential distortion. The study showed that vortex strength, generator scale, and secondary flow field structure have a complicated and interrelated influence on the engine face distortion, over and above the initial geometry and arrangement of the generators. The installed vortex generator performance was found to be a function of three categories of variables: the inflow conditions, the aerodynamic characteristics associated with the inlet duct, and the design parameters related to the geometry, arrangement, and placement of the vortex generators within the outlet duct itself.
Document ID
19920041143
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Anderson, Bernhard H.
(NASA Lewis Research Center Cleveland, OH, United States)
Huang, Pao S.
(NASA Lewis Research Center Cleveland, OH, United States)
Paschal, William A.
(NASA Lewis Research Center Cleveland, OH, United States)
Cavatorta, Enrico
(Dee Howard Co. San Antonio, TX, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-0152
Accession Number
92A23767
Distribution Limits
Public
Copyright
Other

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