Method for controlling transonic-speed buffering by tangential narrow-slit gas blowing and gas blowing device

Abstract

The invention discloses a method and a device for controlling transonic-speed buffering by tangential narrow-slit gas blowing. The method is characterized in that a shrinkage tube or a shrinkage / expansion tube is adopted to blow gas to transonic-speed shock wave positions of various wings at an outlet end of the shrinkage tube or the shrinkage / expansion tube and positions parallel to various wing surfaces to control transonic-speed buffering, wherein starting from the most downstream position of the shock wave location, the gas-blowing positions are gradually moved towards the upstream and certainly exceed the most upstream position of the shock wave location until nearly close to a front edge position; within the range, control effect of the gas-blowing positions on buffering is reached by virtue of a test or a numerical simulation method, and optimized positions are obtained. According to the invention, with the goal of delaying a transonic-speed buffering boundary and slowing down buffering load, a tangential narrow-slit gas blowing control method taking the shrinkage tube or the shrinkage / expansion tube as a gas-blowing device has the advantages of being simple in device, relatively small in disturbance on flow fields, smoothly transitional, free of separation flow and capable of reducing energy loss.

Description

technical field [0001] The invention relates to a tangential slit blowing technology for controlling transonic buffeting, which belongs to the flow control technology in the field of aerospace, in particular to a method for controlling transonic chattering by tangential slit blowing and blowing technology. gas device. Background technique [0002] Under the condition of transonic flight, the shock wave / boundary layer interference on the upper surface of the wing of the aircraft, the missile wing of the missile and the rotor of the rotorcraft can cause the self-sustained oscillation of the shock wave, thereby forming an oscillating load on various wing surfaces, not only It will cause buffeting problems of the aircraft, reduce the comfort of the ride, and cause structural fatigue, and even cause flight accidents. For this reason, the transonic buffeting boundary has always been one of the main factors limiting the flight envelope in the flight test of civil aircraft. With t...

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Problems solved by technology

[0003] Previous studies have shown that using grooves, leading edge vortex generators, shock wave control bulges, etc. to passively suppress shock wave buffeting will receive better results in the design state, but it will often fail when the design conditions deviate from it. adverse effects, or even worsen the aerodynamic characteristics of the basic airfoil; active excitation methods such as trailing edge deflection devices, resonant rudder surfaces, or flap swings are used to suppress buffeting, and the control rate is often very complicated, and the size of the control rudder itself is large, which is difficult for The driving force requirement is high, and additional driving energy will be paid

Therefore, the previous control technology has not really been applied to aerospace products

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