Active flow control testing unit for air inlet duct of high-speed wind tunnel

Abstract

An active flow control testing unit for an air inlet duct of a high-speed wind tunnel comprises a reducing bend, a total pressure measuring section, a static pressure measuring section, quick joints, an elbow and an electric regulating valve. The front end of the reducing bend is connected with a model, and the rear end of the reducing bend is connected with the total pressure measuring section through a flange. The front end of the total pressure measuring section is connected with the rear end of the reducing bend through a flange, and the rear end of the total pressure measuring section is connected with the front end of the static pressure measuring section through a flange. The rear end of the static pressure measuring section is connected with the front end of a first high-pressure wire braided rubber pipe, the rear end of the first high-pressure wire braided rubber pipe is connected with the first quick joint, and the rear end of the first quick joint is connected with one end of the elbow. The active flow control testing unit for the air inlet duct or the high-speed wind tunnel is simple in structure and convenient in operation, the total pressure measuring section and the static pressure measuring section are used for measuring parameters of flow injected into or pumped out, and trace flow of the air injected into or pumped out of the model air inlet duct of an airplane can be controlled and measured accurately.

Description

Technical field [0001] The invention relates to an aerodynamic experiment equipment for aviation, in particular to a high-speed wind tunnel inlet active jet / suction flow control test device, which is used to accurately control and measure the injection or extraction of an aircraft inlet model A small amount of air flow. Background technique [0002] Current and future combat aircraft (including unmanned combat / attack aircraft) reduce weight and improve stealth performance by shortening the length of the inlet and increasing its curvature, but this will separate the airflow boundary layer in the inlet and cause the engine inlet flow. The severe distortion of the field greatly reduces the net thrust and even causes the engine to stall. In order to solve this problem, in addition to the passive flow control method in the inlet, the high-speed wind tunnel inlet active jet / suction flow control experiment provides an effective active flow control experiment method, in order to reduce ...

AI Technical Summary

Problems solved by technology

[0002] Current and future combat aircraft (including unmanned combat / attack aircraft) reduce weight and improve stealth performance by shortening the length of the air inlet and increasing its curvature, but this will cause the separation of the airflow boundary layer in the air inlet and cause the engine inlet flow. Serious distortion of the field, greatly reducing the net thrust, and even causing the engine to stall

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