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Water tunnel visualization of the vortex flows of the F-15Flow visualization studies were conducted in a diagnostic water tunnel to provide details of the wing, glove, and forebody vortex flow fields of the F-15 aircraft over a range of angles of attack and sideslip. Both the formation and breakdown of the vortex flow as a function of angle of attack and sideslip are detailed for the basic aircraft configuration. Additional tests showed that the wing upper surface vortex flows were sensitive to variations in an inlet mass flow ratio and an inlet cowl deflection angle. Two lengthened forebodies, one with a modified cross-sectional shape, were tested in addition to the basic forebody. Asymmetric forebody vortices were observed at zero sideslip and high angles of attack on each forebody. A large nose boom was added to each of the three forebodies, and it was observed that the turbulent wake shed from the boom disrupted the forebody vortices.
Document ID
19790061312
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Lorincz, D. J.
(Northrop Corp. Hawthorne, Calif., United States)
Friend, E. L.
(NASA Flight Research Center Stability and Control Branch, Edwards, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 79-1649
Meeting Information
Meeting: Atmospheric Flight Mechanics Conference for Future Space Systems
Location: Boulder, CO
Start Date: August 6, 1979
End Date: August 8, 1979
Accession Number
79A45325
Funding Number(s)
CONTRACT_GRANT: NAS4-2526
Distribution Limits
Public
Copyright
Other

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