| 摘要 |
In order to make possible an aircraft of high mechanical strength with a low structural weight and maximum lift performance with a low overall drag, an all-wing composite system is created which, in plan view and end view, exhibits a delta-shaped wing composite. The circumferential rear edge profile is formed such that an acceleration of the flow occurs in the rear region of the profile, which increases the coefficient of lift and prevents boundary-layer separation in the useful incidence-angle range. The departure of the tip vortex wake is made possible at 70 % of the span width in order to ensure a low induced drag in the region of high coefficients of lift. Longitudinal stabilisation is carried out without auxiliary surfaces by means of a specific centre of gravity position, such that the system rises or falls in brief changes in the incident flow, without moving about the pitch axis, and in consequence produces a particularly favourable flight path behaviour.
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