NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Flow Visualization Study of the F-14 Fighter Aircraft ConfigurationWater tunnel studies were performed to qualitatively define the flow field of the F-14. Particular emphasis was placed on defining the vortex flows generated at high angles of attack. The flow visualization tests were conducted in the Northrop water tunnel using a 1/72 scale model of the F-14 with a wing leading-edge sweep of 20 deg. Flow visualization photographs were obtained for angles of attack up to 55 deg and sideslip angles up to 10 deg. The F-14 model was investigated to determine the vortex flow field development, vortex path, and vortex breakdown characteristics as a function of angle of attack and sideslip. Vortex flows were found to develop on the highly swept glove and on the upper surface of the forebody. At 10 deg of sideslip, the windward glove vortex shifted inboard and broke down farther forward than the leeward glove vortex. This asymmetric breakdown of the vortices in sideslip contributes to a reduction in the lateral stability above 20 deg angle of attack. The initial loss of directional stability is a consequence of the adverse sidewash from the windward vortex and the reduced dynamic pressure at the vertical tails.
Document ID
19800024842
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Lorincz, D. J. (Northrop Corp. Hawthorne, CA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NOR-80-150
H-1135
NASA-CR-163098
Accession Number
80N33350
Funding Number(s)
CONTRACT_GRANT: NAS4-2616
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available