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Aerodynamic-structural study of canard wing, dual wing, and conventional wing systems for general aviation applicationsAn analytical aerodynamic-structural airplane configuration study was conducted to assess performance gains achievable through advanced design concepts. The mission specification was for 350 mph, range of 1500 st. mi., at altitudes between 30,000 and 40,000 ft. Two payload classes were studied - 1200 lb (6 passengers) and 2400 lb (12 passengers). The configurations analyzed included canard wings, closely coupled dual wings, swept forward - swept rearward wings, joined wings, and conventional wing tail arrangements. The results illustrate substantial performance gains possible with the dual wing configuration. These gains result from weight savings due to predicted structural efficiencies. The need for further studies of structural efficiencies for the various advanced configurations was highlighted.
Document ID
19850008520
Document Type
Contractor Report (CR)
Authors
Selberg, B. P. (Missouri Univ. Rolla, MO, United States)
Cronin, D. L. (Missouri Univ. Rolla, MO, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1985
Subject Category
AERODYNAMICS
Report/Patent Number
NASA-CR-172529
NAS 1.26:172529
Funding Number(s)
CONTRACT_GRANT: NAG1-26
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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