Supersonic intersecting flow channel and wall surface determination method thereof

Abstract

The invention provides a supersonic intersecting flow channel and a wall surface determination method thereof. The wall surface determination method of the supersonic intersecting flow channel comprises the steps that an outlet boundary and two inlet boundaries are determined according to geometric constraints on a design structure of the supersonic intersecting flow channel; internal wall surface curves of two branches of the supersonic intersecting flow channel are determined by utilizing a second-order continuous curve according to the geometric constraints on the design structure of the supersonic intersecting flow channel; external wall surface curves of the supersonic intersecting flow channel, which correspond to the internal wall surface curves of the two branches, are determined by utilizing a characteristic line method; an upper wall surface curve and a lower wall surface curve of a main flow channel of the supersonic intersecting flow channel are determined by utilizing the characteristic line method; internal wall surfaces of the branch parts are determined according to the internal wall surface curves of the two branch parts; external wall surfaces of the branch parts are determined according to the external wall surface curves; and an upper wall surface and a lower wall surface of the main flow channel are determined according to the upper wall surface curve and the lower wall surface curve of the main flow channel. The supersonic intersecting flow channel designed according to the method provided by the invention can guarantee that the flow is supersonic during the whole course, a flow field of the flow is even and the total pressure loss is low.

Description

technical field [0001] The invention relates to the field of aerodynamic design, in particular to a method for determining a supersonic confluence flow channel and its wall surface. Background technique [0002] With the development of modern aerodynamic research, supersonic flow mixing technology has played an increasingly important role in the field of experimental research. The supersonic intersection channel is a typical component that merges different supersonic flow fields into one supersonic airflow. The supersonic air flow intersection 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 the shock wave, which will reduce the working ability of the air flow. The other is that the interaction between the shock wave and the boundary layer will cause flow separation. , or even block the entire flow channel. [0003] The existing confluence channel design is mainly used for general thr...

AI Technical Summary

Problems solved by technology

The supersonic air flow intersection 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 the shock wave, which will reduce the working ability of the air flow. The other is that the interaction between the shock wave and the boundary layer will cause flow separation. , or even block the entire flow channel

[0003] The existing design of the intersection flow channel is mainly used for general three-way flow. Since the characteristics of supersonic air flow are not considered, shock waves will inevitably appear, resulting in total pressure loss and air flow distortion.

At the same time, the existing design method will also reduce the supersonic air flow to subsonic speed, the flow field is not uniform, and the total pressure loss is very large

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