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Title
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Wing Planform Geometry Effects on Large Subsonic Military Transport Airplanes
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Date
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1978
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Index Abstract
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Coming Soon
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Photo Quality
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Not Needed
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Report Number
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AFFDL TR 78-16
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Creator
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Kulfan, Robert M.
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Vachal, John D.
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Corporate Author
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Boeing Commercial Airplane Company
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Laboratory
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Air Force Flight Dynamics Laboratory
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Date Issued
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1978-02
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Extent
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71
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Identifier
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ADA056124
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Access Rights
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Approved for public release; distribution unlimited
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Distribution Classification
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1
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Contract
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F33615-76-C-3035
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DoD Project
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2404
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DoD Task
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240410
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DTIC Record Exists
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No
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Distribution Change Authority Correspondence
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None
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Abstract
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A Preliminary Design Study of large turbulent flow military transport aircraft has been made. The study airplanes were designed to carry a heavy payload (350,000 lb) for a long range (10,000 nmi). The study tasks included: Wing geometry/cruise speed optimization of a large cantilever wing military transport airplane; Preliminary design and performance evaluation of a strut-braced wing transport airplane; and Structural analyses of large-span cantilever and strut-braced wings of graphite/epoxy sandwich construction (1985 technology). The best cantilever wing planform for minimum takeoff gross weight, and minimum fuel requirements, as determined using statistical weight evaluations, has a high aspect ratio, low sweep, low thickness/chord ratio, and a cruise Mach number of 0.76. A near optimum wing planform with greater speed capability (M = 0.78) has an aspect ratio = 12, quarter chord sweep = 20 deg, and thickness/chord ratio of 0.14/0.08 (inboard/outboard).
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Report Availability
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Full text available
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Provenance
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AFRL/VACA
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Type
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report
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Format
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1 online resource
AFFDLTR78-016.pdf