3results about How to "Increase the maximum lift coefficient" patented technology

This invention discloses a high lift-to-drag ratio, long-endurance, low-speed airfoil, revealing its maximum relative camber, maximum relative thickness, and the curve equations satisfied by its upper and lower edges. The origin of the coordinate system containing the airfoil is defined as the leading edge of the chord. The X-axis coincides with the chord line, pointing from the leading edge to the trailing edge of the airfoil. The Y-axis is perpendicular to the X-axis, pointing in the direction of the airfoil's curvature. The chord length is defined as C; therefore, the maximum relative camber is 6%C, and the maximum relative thickness is 4.5%C. The airfoil of this invention exhibits a higher lift-to-drag ratio and a higher lift coefficient while maintaining a lower drag coefficient. It reduces the weight of the wing structure, and its thin, curved shape results in a smaller internal wing cavity, optimizing aircraft weight while concentrating stress on the structure.

The plasma combined trailing edge suction flow control device for the rotor blades comprises a plurality of blades (1), and nanosecond pulse dielectric barrier discharge plasma exciters (2) are installed at the front edges of the blades and cover the extension length of the whole blades; the tail end of the paddle is provided with an air suction device (3), and the center of an air suction port is A% c away from the front edge. The tail end air suction device (3) comprises a tail end air suction port (3-1), a low-pressure air chamber (3-2) and a connecting pipeline (3-3). When rotor wing type dynamic stall is controlled, the high-frequency nanosecond pulse power supply (4) is used for powering up the nanosecond pulse dielectric barrier discharge plasma exciter (2). The invention further provides a plasma combined trailing edge suction flow control method for the rotor blade. Through combination of plasma excitation and trailing edge air suction, the airfoil upper surface flow field structure can be effectively interfered, the flow separation degree is reduced, the average lift force of the rotor blade is improved, and therefore the performance of the rotor blade is improved.

The present application belongs to the field of air flow, and relates to a blowing flap of a fixed-axle sub flap adaptive spoiler. The blowing flap comprises a fixed wing surface, a fixed rotating shaft, a main flap, a sub flap, a main flap blowing gap, a sub flap blowing gap, a spoiler rotating shaft and a spoiler. The main flap and the sub flap are downwardly deflected at a large angle, the spoiler is downwardly deflected to be attached to the upper surface of the sub flap, the blowing gaps on the sub flap and the main flap work in a certain blowing momentum coefficient matching relationship, the maximum lift coefficient of the aircraft is greatly improved, the lift-drag ratio is very high, and the super-circulation effect is realized.