Abstract
Abstract : The flow about a slender flat-plate delta wing at angle of-attack is represented by replacing the vortex core-feeding sheet system associated with leading edge separation by a force-free concentrated vortex. Secondary flow phenomena near the leading edge are approximated by allowing infinite flow velocity around the leading edge. The problem is reduced to a two-dimensional one by assuming a conical field and using slender wing theory. Computed pressure and lift distribution, vortex position, lift coefficient, and flow patterns are compared with test data and with the theories of Brown and Michael, and Mangler and Smith. The nonlinear characteristics of the lift curve with angle-of-attack and the strong influence of secondary flow simulation on vortex position and pressure distribution are displayed. The vortex is shown to be further inboard than predicted by previous theories and to correlate well with experiment. The nonlinear component of lift, the pressure distribution, and surface flow pattern are also shown to correlate well with experiment. (Author)
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