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Curved flow wind tunnnel test of F-18 aircraftThe curved flow capability of a stability wind tunnel was used to investigate the lateral directional characteristics of an F-18 aircraft. The model is described and the procedures used to obtain and correct the data and a graphical presentation of the results are presented. The results include graphs of lateral directional derivatives versus sideslip or static plots, the lateral directional static stability derivatives versus angle of attack, and finally the lateral directional derivatives versus nondimensional yaw rate for different angles of attack and sideslip. Results are presented for several configurations including complete, complete without vertical tails, complete without horizontal tails, fuselage wing and fuselage alone. Each of these were tested with and without wing leading edge extensions.
Document ID
19820025463
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Lutze, F. H. (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:169345
VPI-AERO-108
NASA-CR-169345
Accession Number
82N33339
Funding Number(s)
CONTRACT_GRANT: NAS1-15080
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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