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Iterative optimal subcritical aerodynamic design code including profile dragA subcritical aerodynamic design computer code has been developed, which uses linearized aerodynamics along with sweep theory and airfoil data to obtain minimum total drag preliminary designs for multiple planform configurations. These optimum designs consist of incidence distributions yielding minimum total drag at design values of Mach number and lift and pitching moment coefficients. Linear lofting is used between airfoil stations. Solutions for isolated transport wings have shown that the solution is unique, and that including profile drag effects decreases tip loading and incidence relative to values obtained for minimum induced drag solutions. Further, including effects of variation of profile drag with Reynolds number can cause appreciable changes in the optimal design for tapered wings. Example solutions are also discussed for multiple planform configurations.
Document ID
19830035244
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kuhlman, J. M.
(Old Dominion University Norfolk, VA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 83-0012
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: Reno, NV
Start Date: January 10, 1983
End Date: January 13, 1983
Accession Number
83A16462
Funding Number(s)
CONTRACT_GRANT: NSG-1357
Distribution Limits
Public
Copyright
Other

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