The High-lift capability of an aircraft, affecting
take-off and landing performance and low-speed maneuverability, plays an
important role in the design of military and commercial aircraft. Improvedhigh-lift performance can lead to increased range and payload as well asdecreased landing speed and field length requirements. The take-off
configuration designed for a high lift-to-drag ratio (L/D) at moderate lift
coefficient is different from the landing configuration designed for high
maximum lift coefficient. Typical high-lift system for transport aircraft often
consisting o f a basic wing with a leading-edge slat and trailing-edge flap
elements is highly efficient aerodynamically, but at the expense of complex
structure and expensive design and maintenance costs. Current design effects
have focused on mechanically simpler which maximum lift occurs is about 23°,
which is slightly larger than that of experiment.
The figures plot the pressure coefficient on the surface
of the elements at 16 angles of attack comparing computational results againstexperimental results. As can be seen from the figure, computed pressure
distribution is in very good agreement with measurements.
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