Ma4-level supersonic speed axisymmetric air inlet channel and method based on adjustable drainage seams

Abstract

The invention discloses an Ma4-level supersonic speed axisymmetric air inlet channel and method based on adjustable flow discharge seams. The air inlet channel comprises an air inlet channel center body, the air inlet channel center body is of a three-level cone structure, a fairing is arranged on the air inlet channel center body, and a channel is arranged between the air inlet channel center body and the fairing. The air inlet channel center body is connected with the fairing through supports, and the supports are distributed in a central symmetry mode. A plurality of rows of drainage seams are formed in the fairing, and the slotting area of the drainage seams is controllable. The air flow is directly discharged out of the air inlet channel by forming the drainage seam in the fairing, the problem of an air flow path does not need to be specially considered, and the structure is simplified; the starting performance of the air inlet channel is improved, the starting Mach number of the air inlet channel is reduced, and work within the Mach number range of 1.5-4 can be achieved; and the flow is adjusted, so that the flow requirements of an engine under different flight working conditions are met.

Description

technical field [0001] The invention relates to a supersonic axisymmetric inlet port based on a controllable switch of a leakage slot, and belongs to the field of aerodynamic design of the inlet port. Background technique [0002] At present, supersonic and hypersonic aircraft have become the focus of attention of various military powers. As one of the main windward components of the air-breathing propulsion system, the performance of the air-intake duct has an important impact on the aerodynamic performance of the air-breathing propulsion system and even the entire aircraft. In order for the aircraft to achieve wide-speed flight from ground take-off to supersonic and even hypersonic speeds, it is required that the inlet should not only work stably in a wide range, but also have high performance in the design state. Inlet design usually takes high flight Mach number as the design point, but at non-design points, the intake port with fixed geometry design will have a bad phe...

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Problems solved by technology

[0005] The purpose of the present invention is to provide a Ma4-level supersonic axisymmetric inlet and method based on adjustable discharge slots, to solve the problem of the existence of a fixed geometry supersonic axisymmetric inlet in a wide speed range (Ma=0-4) Non-starting problem at low Mach number and intake / engine flow mismatch problem

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