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A numerical method for relating two- and three-dimensional pressure distributions on transonic wingsThis paper presents a preliminary design method for determining a wing's design pressure distribution and geometry based on airfoil normal Mach numbers and airfoil loading. In this method, the perturbation velocities in supercritical regions are computed from airfoil transonic normal Mach numbers and include the influence of local sweep, taper, and three-dimensional induced velocities, so that the appearance and strength of shocks can be expected to resemble those of the airfoil. The velocities in subcritical wing regions are scaled first with simple sweep theory, and then to achieve the desired load distribution. The method was applied to the design of an oblique flying wing, using a linear potential method. The required wing area could be reduced by 14 percent using this method rather than simple sweep theory.
Document ID
19900061782
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kroo, Ilan
(Stanford University CA, United States)
Van Der Velden, Alexander J. M.
(Stanford Univ. CA, United States)
Date Acquired
August 14, 2013
Publication Date
September 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 90-3211
Accession Number
90A48837
Funding Number(s)
CONTRACT_GRANT: NCA2-343
Distribution Limits
Public
Copyright
Other

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