Mach number control method of experimental section flow field of continuous transonic wind tunnel

Abstract

The invention relates to a Mach number control method of an experimental section flow field of a continuous transonic wind tunnel. According to the given target Mach number, the rotation speed n of a compressor, the angle beta of a static blade and the position L of a choke finger, the initial states of the angle beta of the static blade and the position L of the choke finger keep unchangeable, and the rotation speed n of the compressor is adjusted to be a target value; after the rotation speed n of the compressor is in place, according to the set of a specific experiment, the angle beta of the static blade is adjusted to be a target value, and then the position L of the choke finger is adjusted to be a target value; when the rotation speed n of the compressor, the angle beta of the static blade and the position L of the choke finger are adjusted to be the target values, the Mach number, measured in real time, of the experimental section is compared with the target Mach number, and then the rotation speed of the compressor, the angle of the static blade and the position of the choke finger are adjusted according to the deviation value until the actual Mach number is close to the target Mach number. A thought is provided for controlling the Mach number of the experimental section flow field of the continuous transonic wind tunnel, and technical support is provided for ensuring smooth development of national advanced aircrafts.

Description

technical field [0001] The invention belongs to the field of aerospace, and in particular relates to a method for controlling the Mach number of a flow field in a continuous transonic wind tunnel experiment section. Background technique [0002] The continuous transonic wind tunnel is a kind of backflow wind tunnel. The flow field in the experimental section is a transonic flow field, which can carry out a large number of blowing experiments continuously. Its structure is as follows: figure 1 shown. Through this wind tunnel, aircraft type selection experiments can be carried out, providing technical support for advanced airfoil type selection and advanced aircraft design. [0003] The continuous transonic wind tunnel has the following characteristics: [0004] 1) Dynamic experiment [0005] The wind tunnel can continuously provide a stable experimental flow field (stable Mach number), and the continuous movement of the experimental model can be realized through a certain ...

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Problems solved by technology

"Experimental Fluid Mechanics" in the fourth issue of 2010, "NF-6 Wind Tunnel Mach Number Closed-loop Control System Design Research" through several graphs briefly introduces the Mach number control method, and then explains it with a flow chart, and finally Some control effects are given, but it does not involve the construction idea of ​​continuous transonic wind tunnel Mach number control, the corresponding system equipment and control methods, etc.

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