NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Transonic wind-tunnel tests of an F-8 airplane model equipped with 12 and 14-percent thick oblique wingsAn experimental investigation was conducted in the Ames 14-foot transonic wind tunnel to study the aerodynamic performance and stability characteristics of a 0.087-scale model of an F-8 airplane fitted with an oblique wing. Two elliptical planform (axis ratio = 8:1) wings, each having a maximum thickness of 12 and 14 percent, were tested. Longitudinal stability data were obtained with no wing and with each of the two wings set at sweep angles of 0, 45, and 60 deg. Lateral directional stability data were obtained for the 12 percent wing only. Test Mach numbers ranged from 0.6 to 1.2 in the unit Reynolds number range from 11.2 to 13.1 million per meter. Angles of attack were between -6 and 22 deg at zero sideslip. Angles of sideslip were between -6 and +6 deg for two angles of attack, depending upon the wing configuration.
Document ID
19760012054
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
October 1, 1975
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-TM-X-62478
A-6259
Accession Number
76N19142
Funding Number(s)
PROJECT: RTOP 505-11-12
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