Airfoil current control device

Abstract

The invention relates to an airfoil flow control device. The airfoil flow control device is arranged on the upper surface of the main airfoil of an airplane near the front edge of the airfoil. The device consists of a fundamental frequency Gershgorim band and a subharmonic frequency Gershgorim band which are arranged in parallel; both the fundamental frequency Gershgorim band and the subharmonic frequency Gershgorim band are in a sawtooth shape; during the taking off stage, a front flap extends the airfoil flow control device, thereby controlling the boundary layer of the airfoil to fast transit and form an onflow boundary layer used for restraining or eliminating the separation of the boundary layers, thereby effectively improving the life force of the airfoil; during cruising flying, the front flap of the airfoil resets to cover the device, thus leading the device to be out of use and leading the boundary layer of the airfoil to maintain a layer flow during the cruising stage, so as to reduce the friction resistance at the airfoil surface and improve the lift-drag ratio. The airfoil flow control device has the advantages of simple structure, light weight and convenient for being maintained, can solve the separation problem of the boundary layers of the airfoil surfaces during the taking off state of the airplane under the situations of not increasing the weight of the airplane and the power; besides, the airfoil flow control device also avoids the increasing problem of the friction resistance brought by the transition of the boundary layers of the airfoil surfaces during the cruising flying stage.

Description

technical field [0001] The invention relates to a wing flow control device, which is used for solving the problem of lift reduction caused by the separation of the boundary layer of the wing surface during the take-off or landing stage of an aircraft. Background technique [0002] During the take-off phase, the aircraft often adopts such as figure 1 In the manner shown, the wing 101 cooperates with the leading edge flap 102 and the trailing edge flap 103 and increases the flight angle of attack to increase the lift force, mainly because the speed of the large aircraft is low during the takeoff stage and the dynamic pressure head of the airflow is relatively low , is not enough to provide lift, so it is necessary to increase the wing area and increase the flight angle of attack to increase the lift by increasing the lift device such as the front and rear flaps. However, flying at high angles of attack causes the wing boundary layer to separate, resulting in a loss of lift. ...

AI Technical Summary

Problems solved by technology

[0003] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a wing flow control device, which has a simple structure and is easy to maintain, and can simultaneously solve the lift reduction caused by the separation of the boundary layer of the wing surface during the take-off or landing phase of the aircraft. and the problem of increased frictional resistance caused by the transition of the boundary layer of the wing surface during the cruise phase of the aircraft

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