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A Transonic Wind-Tunnel Investigation of a Seaplane Configuration having a 40 Deg Sweptback Wing, TED No. NACA DE 387During the course of an aerodynamic loads investigation of a model of the Martin XP6M-1 flying boat in the.Langley 16-foot transonic tunnel, longitudinal-aerodynamic-performance information was obtained. Data were obtained at speeds up to and exceeding those anticipated for the seaplane in level flight and included the Mach number range from 0.84. to 1.09. The angle of attack was varied from -2deg to 6deg and the average Reynolds number, based on wing mean aerodyn&ic chord, was about 3.7 x 10(exp 6). This seaplane, although not designed to maintain level flight at Mach numbers beyond the force break, was found to have a transonic drag-rise coefficient of 0.0728, with an accompanying drag-rise Mach number of about 0.85. A large portion of the.drag rise and the relatively low value of drag-rise Mach number result from the axial coincidence of the maximum areas of the principal airplane components.
Document ID
20050029376
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Hieser, Gerald
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Kudlacik, Louis
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Gray, W. H.
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 22, 2013
Publication Date
April 6, 1956
Subject Category
Aerodynamics
Report/Patent Number
Rept-4960
NACA-RM-SL55D07
Report Number: Rept-4960
Report Number: NACA-RM-SL55D07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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