Supersonic flow distribution channel and wall surface determination method thereof

Abstract

The invention provides a supersonic flow distribution channel and a wall surface determination method thereof. The wall surface determination method of the supersonic flow distribution channel comprises the steps that positions and flow directions of an inlet boundary and a plurality of outlet boundaries are determined according to geometric constraints on a design structure of the supersonic flow distribution channel, and a first wall surface curve, a second wall surface curve and a third wall surface curve are determined by utilizing a characteristic line method; wall surface curves of branch flow channels are determined in combination with a second-order continuous curve; a lower wall surface curve of a main flow channel is determined by the first wall surface curve and the second wall surface curve, and a lower wall surface of the main flow channel is determined by the lower wall surface curve of the main flow channel; an upper wall surface of the main flow channel is determined by the third wall surface curve; and wall surfaces of the branch flow channels are determined by the wall surface curves of the branch flow channels. The supersonic flow distribution channel determined according to the method has the advantages that internal flow field parameters can be controlled and shock waves cannot be produced in the flow distribution channel, so high-efficiency and low-resistance flow distribution of supersonic flow is realized; and the channel can be freely turned according to design requirements after the flow is distributed.

Description

technical field [0001] The invention relates to the field of aerodynamic design, in particular to a method for determining a supersonic split flow channel and its wall surface. Background technique [0002] With the development of modern aerodynamics research, supersonic flow splitting technology has played an increasingly important role in the field of experimental research. The supersonic flow splitter is a typical component that divides the supersonic flow field into two or more supersonic airflows. The shunted supersonic airflow is easy to generate shock waves, and its impact mainly includes two aspects. One is that there will be a total pressure loss after passing through the shock wave, which will reduce the working ability of the airflow. Second, the interaction between the shock wave and the boundary layer will cause Flow separation, or even blockage of the entire flow channel. [0003] The existing shunt channels are mainly three-way or multi-way for general fluid...

AI Technical Summary

Problems solved by technology

The shunted supersonic airflow is easy to generate shock waves, and its impact mainly includes two aspects. One is that there will be a total pressure loss after passing through the shock wave, which will reduce the working ability of the airflow. Second, the interaction between the shock wave and the boundary layer will cause Flow separation, or even blockage of the entire flow channel

[0003] The existing shunt channels are mainly used for general fluid flow with three-way or multi-way. Since the characteristics of supersonic gas flow are not considered, shock waves will inevitably appear, resulting in total pressure loss and airflow distortion.

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