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Aerodynamic characteristics of an F-8 aircraft configuration with a variable camber wing at Mach numbers from 1.5 to 2.0A 0.1-scale model of an F-8 aircraft was tested over a range of Mach numbers from 1.5 to 2.0. Reynolds number of 4.12 million was based on wing mean-aerodynamic chord for angles of attack varying from -2 deg to +12 deg. The model was equipped with an advanced-technology-conformal-variable-camber wing (ATCVCW) having simple hinge flaps. Data were also obtained for the model equipped with the basic F-8 wing and conventional flaps. Model variables included aileron and wing trailing edge deflections and horizontal tail incidence. The ATCVCW configuration produced slight improvements in lift-curve slope, drag, and static longitudinal stability over that of the basic F-8 wing configuration. Flap effectiveness was essentially the same for both wings.
Document ID
19780008119
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Boltz, F. W. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1977
Subject Category
Aircraft Stability And Control
Report/Patent Number
A-7141
NASA-TM-73271
Accession Number
78N16062
Funding Number(s)
PROJECT: RTOP 505-11-41
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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