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Transonic lateral and longitudinal control characteristics of an F-8 airplane model equipped with an oblique wingThe aerodynamic stability and control characteristics of a 0.087-scale model of an F-8 airplane fitted with an oblique wing was studied. The wing had an elliptical planform (axis ratio = 8:1), a maximum thickness of 12 percent, and was tested at three sweep angles, 0, 45, and 60 deg. Six-component force and moment data were measured at zero sideslip for angles of attack between -6 and +16 deg, with the left and right ailerons deflected one at a time at angles between -14 deg and +14. Further tests were made with the horizontal tail deflected -5 and +2.5 deg. Test Mach numbers ranged from 0.6 to 1.4 at a Reynolds number of 20 million/m.
Document ID
19760015098
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Smith, R. C. (NASA Ames Research Center Moffett Field, CA, United States)
Jones, R. T. (NASA Ames Research Center Moffett Field, CA, United States)
Summers, J. L. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1976
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
A-6434
NASA-TM-X-73103
Accession Number
76N22186
Funding Number(s)
PROJECT: RTOP 505-11-12
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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