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A Three-Dimensional Boundary-Layer Method for Flow over Delta Wings with Leading-Edge Separation
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Abstract
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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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.Also In
References
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