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Two-dimensional separated wake modeling and its use to predict maximum section lift coefficientA technique for computing the lift of separating multielement airfoils in incompressible flow is presented. The procedure employs repeated application of a panel method to solve for the separated wake displacement surface using entirely inviscid boundary conditions. Results are presented that compare computed pressure distributions with those measured in the wind tunnel for airfoils with one, two, and four elements with separation on each element. A method employing this technique is presented which shows promise in predicting airfoil section lift through stall.
Document ID
19780038681
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Henderson, M. L.
(Boeing Commercial Airplane Co. Seattle, Wash., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 78-156
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Huntsville, AL
Start Date: January 16, 1978
End Date: January 18, 1978
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
78A22590
Funding Number(s)
CONTRACT_GRANT: NAS1-14742
Distribution Limits
Public
Copyright
Other

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