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A three-dimensional boundary-layer method for flow over delta wings with leading-edge separation (1985)

Woodson, S. H. ; Dejarnette, F. R.

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Publication Date: 2019-06-28

Description: 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-field 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.

Keywords: AERODYNAMICS

Type: SAE PAPER 851818

Format: text

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