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Stability and transition on swept wingsThis paper describes the extension and application of the Parabolized Stability Equations (PSE) to the stability and transition of the supersonic three-dimensional laminar boundary layer on a swept wing. The problem formulation uses a general coordinate transformation for arbitrary curvilinear body-fitted computational grids. Some testing using these coordinates is briefly described to help validate the software used for the investigation. The disturbance amplitude ratios as a function of chord position for supersonic (Mach 1.5) boundary layers on untapered, untwisted wings of different sweep angles are then presented and compared with those obtained from local parallel analyses.
Document ID
19930036193
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Stuckert, Greg
(DynaFlow, Inc. Columbus, OH, United States)
Herbert, Thorwald
(Ohio State Univ. Columbus, United States)
Esfahanian, Vahid
(DynaFlow, Inc. Columbus, OH, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-0078
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 11, 1993
End Date: January 14, 1993
Sponsors: AIAA
Accession Number
93A20190
Funding Number(s)
CONTRACT_GRANT: NAS2-13513
CONTRACT_GRANT: F49620-92-J-0271
Distribution Limits
Public
Copyright
Other

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