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Juncture flow improvement for wing/pylon configurations by using CFD methodologyTransonic flow field around a fighter wing/pylon configuration was simulated by using an implicit upwinding Navier-Stokes flow solver (F3D) and overset grid technology (Chimera). Flow separation and local shocks near the wing/pylon junction were observed in flight and predicted by numerical calculations. A new pylon/fairing shape was proposed to improve the flow quality. Based on numerical results, the size of separation area is significantly reduced and the onset of separation is delayed farther downstream. A smoother pressure gradient is also obtained near the junction area. This paper demonstrates that computational fluid dynamics (CFD) methodology can be used as a practical tool for aircraft design.
Document ID
19930039267
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gea, Lie-Mine
(McDonnell Douglas Aerospace Systems Co. Long Beach, CA, United States)
Chyu, Wei J.
(NASA Ames Research Center Moffett Field, CA, United States)
Stortz, Michael W.
(NASA Ames Research Center Moffett Field, CA, United States)
Chow, Chuen-Yen
(Colorado Univ. Boulder, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-0522
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
93A23264
Funding Number(s)
CONTRACT_GRANT: NCC2-630
Distribution Limits
Public
Copyright
Other

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