NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Water-tunnel study results of a TF/A-18 and F/A-18 canopy flow visualizationA water tunnel study examining the influence of canopy shape on canopy and leading edge extension flow patterns was initiated. The F/A-18 single-place canopy model and the TF/A-18 two place canopy model were the study subjects. Plan view and side view photographs showing the flow patterns created by injected colored dye are presented for 0 deg and 5 deg sideslip angles. Photographs taken at angle of attack and sideslip conditions correspond to test departure points found in flight test. Flight experience has shown that the TF/A-18 airplane departs in regions where the F/A-18 airplane is departure-resistant. The study results provide insight into the differences in flow patterns which may influence the resulting aerodynamics of the TF/A-18 and F/A-18 aircraft. It was found that at 0 deg sideslip, the TF/A-18 model has more downward flow on the sides of the canopy than the F/A-18 model. This could be indicative of flow from the leading edge extension (LEX) vortexes impinging on the sides of the wider TF/A-18 canopy. In addition, the TF/A-18 model has larger areas of asymmetric separated and unsteady flow on the LEXs and fuselage, possibly indicating a lateral and directional destabilizing effect at the conditions studied.
Document ID
19900013216
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Johnson, Steven A. (NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Fisher, David F. (NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
September 8, 2013
Publication Date
March 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:101705
H-1570
NASA-TM-101705
Accession Number
90N22532
Funding Number(s)
PROJECT: RTOP 533-02-01
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