The Attached Flow over a Slender Delta Wing with Leading-Edge Flaps.

摘要

The flow over a delta wing with leading-edge flaps is considered within the framework of slender-body theory. To avoid flow separation at the leading edges of the flaps a Kutta condition is applied there which uniquely determines the angle of attack for a given flap configuration. The lift coefficient and lift-dependent drag factor are then calculated for this condition and compared with the prediction of slender thin-wing theory, in which the wing boundary condition is fully linearized. (Author)