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Lift, Drag, and Pitching Moment of Low-Aspect-Ratio Wings at Subsonic and Supersonic Speeds: Triangular Wing of Aspect Ratio 2 with NACA 0005-63 Thickness Distribution, Cambered and Twisted for a Trapezoidal Span Load DistributionA wing-body combination having a plane triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution in streamwise planes, and twisted and cambered for a trapezoidal span load distribution has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.60 to 0.90 and 1.30 to 1.70 at a Reynolds number of 3.0 million. The variations of the characteristics with Reynolds number are also shown for several Mach numbers.
Document ID
20030066981
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Smith, Willard G. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Phelps, E. Ray (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Date Acquired
September 7, 2013
Publication Date
February 5, 1951
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-A50K27a
Report Number: NACA-RM-A50K27a
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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