A hypersonic convex-to-circular converging inlet and its design method

Abstract

The invention discloses a high-supersonic-speed internal contraction air intake channel gradually changed from the convex shape into the round shape and a design method thereof. According to the high-supersonic-speed internal contraction air intake channel gradually changed from the convex shape into the round shape, the middle of a lip plate of the air intake channel gradually changed from the convex shape into the round shape is provided with an upward protruding part, an inlet of the air intake channel is in the convex shape, and the air intake channel contracts towards an outlet, is gradually changed into the round shape and then is connected with a circular-cross-section equal straight isolation section equal to the air intake channel in area; an internal conical surface controllablein compression surface Mach number, a central body of a uniform flow movable angle variable cross section, and a datum flow field are obtained through a characteristic line method, and reverse streamline tracing is conducted according to the round outlet of the air intake channel; the upward protruding part is additionally arranged at the inlet based on the original rectangle and extends to the central body, accordingly, matching is conducted on the natural outlet area obtained through convex inlet streamline tracing, and a round outlet of which the area is equal to that of the convex inlet isobtained; and after streamline fitting and boundary layer correcting are conducted, the final air intake channel changed from the convex shape into the round shape is obtained. According to the high-supersonic-speed internal contraction air intake channel gradually changed from the convex shape into the round shape and the design method thereof, on the premise that design point shock wave sealingis ensured, starting of the internal contraction air intake channel is substantially improved through the upper convex overflow design measure designed by the streamline tracing technology.

Description

technical field [0001] The invention relates to a hypersonic convex-turned-circular inner shrinkage inlet and a design method thereof, belonging to the technical field of hypersonic inlets. Background technique [0002] Scramjet technology is the third revolution in the history of human aviation after the Wright brothers' aircraft and jet propulsion. The propulsion device or the combined propulsion device based on the propulsion device utilizes the compressed air in the intake port to provide sufficient air and a qualified flow field for engine combustion. [0003] The performance of the hypersonic inlet is crucial to the normal operation of the scramjet engine and the entire aircraft. A well-designed hypersonic inlet should not only have the requirements of light structure, high compression efficiency, low resistance, and high-quality airflow provided to the combustion chamber, but also require reliable starting. Once the air inlet fails to start, the engine will lose thr...

AI Technical Summary

Problems solved by technology

Among them, blowing type flow control requires a special high-pressure compressed air device and control pipeline, and boundary layer suction type control method loses flow

The biggest problem with these two types of flow control is that the position of the flow control is fixed, which can be extremely inefficient once the intake port is stuck inactive

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