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.
Method for controlling transonic-speed buffering by tangential narrow-slit gas blowing and gas blowing device
2015-12-23
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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