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Wing planform effects at supersonic speeds for an advanced fighter configurationFour advanced fighter configurations, which differed in wing planform and airfoil shape, were investigated in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.60, 1.80, 2.00, and 2.16. Supersonic data were obtained on the four uncambered wings, which were each attached to a single fighter fuselage. The fuselage geometry varied in cross-sectional shape and had two side-mounted, flow-through, half-axisymmetric inlets. Twin vertical tails were attached to the fuselage. The four planforms tested were a 65 deg delta wing, a combination of a 20 deg trapezoidal wing and a 45 deg horizontal tail, a 70 deg/30 deg cranked wing, and a 70 deg/66 deg crank wing, where the angle values refer to the leading-edge sweep angle of the lifting-surface planform. Planform effects on a single fuselage representative of an advanced fighter aircraft were studied. Results show that the highly swept cranked wings exceeded the aerodynamic performance levels, at low lift coefficients, of the 65 deg delta wing and the 20 deg trapezoidal wing at trimmed and untrimmed conditions.
Document ID
19840012418
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Wood, R. M. (NASA Langley Research Center Hampton, VA, United States)
Miller, D. S. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-2269
NAS 1.60:2269
L-15706
Accession Number
84N20486
Funding Number(s)
PROJECT: RTOP 505-43-23-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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