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A water tunnel flow visualization study of the F-15Water tunnel studies were performed to qualitatively define the flow field of the F-15 aircraft. Two lengthened forebodies, one with a modified cross-sectional shape, were tested in addition to the basic forebody. Particular emphasis was placed on defining vortex flows generated at high angles of attack. The flow visualization tests were conducted in the Northrop diagnostic water tunnel using a 1/48-scale model of the F-15. Flow visualization pictures were obtained over an angle-of-attack range to 55 deg and sideslip angles up to 10 deg. The basic aircraft configuration was investigated in detail to determine the vortex flow field development, vortex path, and vortex breakdown characteristics as a function of angle of attack and sideslip. Additional tests showed that the wing upper surface vortex flow fields were sensitive to variations in inlet mass flow ratio and inlet cowl deflection angle. Asymmetries in the vortex systems generated by each of the three forebodies were observed in the water tunnel at zero sideslip and high angles of attack.
Document ID
19790010115
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Lorincz, D. J.
(Northrop Corporate Labs. Hawthorne, CA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1978
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-CR-144878
NOR-78-176
Report Number: NASA-CR-144878
Report Number: NOR-78-176
Accession Number
79N18286
Funding Number(s)
CONTRACT_GRANT: NAS4-2526
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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