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F-14A aircraft high-speed flow simulationsA model of the Grumman/Navy F-14A aircraft was developed for analyses using the NASA/Grumman Transonic Wing-Body Code. Computations were performed for isolated wing and wing fuselage glove arrangements to determine the extent of aerodynamic interference effects which propagate outward onto the main wing outer panel. Additional studies were conducted using the full potential analysis, FLO 22, to calibrate any inaccuracies that might accrue because of small disturbance code limitations. Comparisons indicate that the NASA/Grumman code provides excellent flow simulations for the range of wing sweep angles and flow conditions that will be of interest for the upcoming F-14 Variable Sweep Flight Transition Experiment.
Document ID
19850015391
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Boppe, C. W. (Grumman Aerospace Corp. Bethpage, NY, United States)
Rosen, B. S. (Grumman Aerospace Corp. Bethpage, NY, United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-172559
NAS 1.26:172559
Accession Number
85N23702
Funding Number(s)
CONTRACT_GRANT: NAS1-14732
PROJECT: RTOP 505-45-63
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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