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Integrated technology wing design studyThe technology development costs and associated benefits in applying advanced technology associated with the design of a new wing for a new or derivative trijet with a capacity for 350 passengers and maximum range of 8519 km, entering service in 1990 were studied. The areas of technology are: (1) airfoil technology; (2) planform parameters; (3) high lift; (4) pitch active control system; (5) all electric systems; (6) E to 3rd power propulsion; (7) airframe/propulsion integration; (8) graphite/epoxy composites; (9) advanced aluminum alloys; (10) titanium alloys; and (11) silicon carbide/aluminum composites. These technologies were applied to the reference aircraft configuration. Payoffs were determined for block fuel reductions and net value of technology. These technologies are ranked for the ratio of net value of technology (NVT) to technology development costs.
Document ID
19840025331
Document Type
Contractor Report (CR)
Authors
Hays, A. P. (Lockheed-California Co. Burbank, CA, United States)
Beck, W. E. (Lockheed-California Co. Burbank, CA, United States)
Morita, W. H. (Lockheed-California Co. Burbank, CA, United States)
Penrose, B. J. (Lockheed-California Co. Burbank, CA, United States)
Skarshaug, R. E. (Lockheed-California Co. Burbank, CA, United States)
Wainfan, B. S. (Lockheed-California Co. Burbank, CA, United States)
Date Acquired
September 4, 2013
Publication Date
August 1, 1984
Subject Category
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
NASA-CR-3586
NAS 1.26:3586
LR-30000
Funding Number(s)
CONTRACT_GRANT: NAS1-16273
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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