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.
A Three-Dimensional Boundary-Layer Method for Flow over Delta Wings with Leading-Edge Separation
Sae Technical Papers
Aerospace Technology Conference and Exposition ; 1985
1985-10-01
Aufsatz (Konferenz)
Englisch
Three-dimensional flow over wings with leading-edge vortex separation
Tema Archiv | 1980
|On Slender Delta Wings with Leading-edge Separation
NTRS | 1955
|On slender Delta wings with leading-edge separation
Engineering Index Backfile | 1955
|