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Numerical optimization - An assessment of its role in transport aircraft aerodynamic design through a case studyAn efficient transonic wing design procedure based upon numerical optimization together with three-dimensional transonic methods has been developed and used to design an advanced transport wing. The method development included an examination of the use of both full potential and extended small disturbance analysis codes and demonstrated that the former formulation was more reliable. In either case, the design procedure is economical and easy to use. Design verification in a unique semi-span test arrangement demonstrated that the design method produced a wing which satisfied the study design requirements. However, aeroelastic deformation of the wing occurred during the wind tunnel test. The computational methods used in the design procedure were employed to assess the effect of the aeroelastic deformation. The paper concludes with an evaluation of the design procedure and recommendation for its improvement.
Document ID
19810027200
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Lores, M. E.
(Lockheed-Georgia Co. Marietta, GA, United States)
Smith, P. R.
(Lockheed-Georgia Co. Marietta, Ga., United States)
Large, R. A.
(USAF, Flight Dynamics Laboratory, Wright-Patterson AFB Ohio, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1980
Subject Category
Aircraft Design, Testing And Performance
Meeting Information
Meeting: International Council of the Aeronautical Sciences, Congress
Location: Munich
Country: Germany
Start Date: October 12, 1980
End Date: October 17, 1980
Sponsors: International Council of the Aeronautical Sciences
Accession Number
81A11604
Funding Number(s)
CONTRACT_GRANT: F33615-78-C-3014
Distribution Limits
Public
Copyright
Other

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