A Three-Dimensional Boundary-Layer Method for Flow over Delta Wings with Leading-Edge Separation

851818

10/01/1985

Event
Aerospace Technology Conference and Exposition
Authors Abstract
Content
A three-dimensional, Laminar boundary-layer method is applied to the incompressible flow over a slender delta wing at incidence. The predictor-corrector finite-difference scheme of Matsuno is used to difference the governing equations. The method has the advantages that no iterations are required to advance the solution and the cross-flow derivatives are formed independent of the cross-flow direction. The difference scheme is demonstrated to yield accurate numerical results when compared to the exact solution of the three-dimensional boundary-layer equations for parabolic flow over a moving flat plate. The method is applied to delta wings of various sweep angles at angles of attack up to 20 deg., with the inviscid solution determined using a higher-order, three-dimensional panel method.
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DOI
https://doi.org/10.4271/851818
Pages
16
Citation
Woodson, S., and DeJarnette, F., "A Three-Dimensional Boundary-Layer Method for Flow over Delta Wings with Leading-Edge Separation," SAE Technical Paper 851818, 1985, https://doi.org/10.4271/851818.
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Publisher
Published
Oct 1, 1985
Product Code
851818
Content Type
Technical Paper
Language
English