Accession Number:

ADA056124

Title:

Wing Planform Geometry Effects on Large Subsonic Military Transport Airplanes.

Descriptive Note:

Final technical rept. Mar 76-Feb 77,

Corporate Author:

BOEING COMMERCIAL AIRPLANE CO SEATTLE WASH

Personal Author(s):

• Kulfan,Robert M.
• Vachal,John D.

Report Date:

1978-02-01

Pagination or Media Count:

66.0

Abstract:

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 geometrycruise 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 graphiteepoxy 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 thicknesschord 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 thicknesschord ratio of 0.140.08 inboardoutboard.

Descriptors:

• *JET TRANSPORT AIRCRAFT
• *AERONAUTICAL ENGINEERING
• *WING BODY CONFIGURATIONS
• OPTIMIZATION
• STRUCTURAL ANALYSIS
• EFFICIENCY
• EPOXY LAMINATES
• FUEL CONSUMPTION
• GEOMETRY
• WINGS
• GRAPHITED MATERIALS
• WEIGHT REDUCTION
• STRUTS
• SANDWICH CONSTRUCTION
• LIFT TO DRAG RATIO

Subject Categories:

• Transport Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE