Wing Planform Geometry Effects on Large Subsonic Military Transport Airplanes

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Report Number: AFFDL TR 78-16
Author(s): Kulfan, Robert M., Vachal, John D.
Corporate Author(s): Boeing Commercial Airplane Company
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1978-02
Pages: 71
Contract: F33615-76-C-3035
DoD Project: 2404
DoD Task: 240410
Identifier: ADA056124

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).

Provenance: AFRL/VACA

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