Flow control ejection system for aircraft model low-speed wind tunnel test

A wind tunnel experiment and flow control technology, which is applied to the testing of machines/structural components, instruments, and measuring devices, can solve problems such as limited intake flow, affecting experimental results, and congestion at the exhaust outlet of the main intake pipe. To achieve the effect of increasing the intake flow and improving the authenticity
CN109596302AActive Publication Date: 2019-04-09XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
Publication Date
2019-04-09

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Abstract

The invention discloses a flow control ejection system for an aircraft model low-speed wind tunnel test. When the aircraft model low-speed wind tunnel test is carried out, a high-pressure air intake nozzle recovers most of the high-pressure airflow sprayed by a high-pressure spray nozzle, the high-pressure airflow enters a recovery pressurization device for pressurization and returns to a high-pressure air tank through a one-way valve, and the main airflow and a small part of the high-pressure airflow are discharged through an outlet of a main air intake pipeline. Since most of the high-pressure airflow is recovered and does not flow through the outlet of the main air intake pipeline, the congestion of the outlet of the main air intake pipeline cannot be caused, the air intake flow of themain air intake pipeline is increased, the simulated flow of the main air intake pipeline in the aircraft model low-speed wind tunnel test can be increased to reach 100% of the design flow, and thus the real working condition can be more closely approximated, and the authenticity of the test can be improved.
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Description

technical field

[0001] The invention relates to the technical field of aircraft model low-speed wind tunnel experiments, in particular to a flow control injection system for aircraft model low-speed wind tunnel experiments. Background technique

[0002] In the low-speed wind tunnel experiment of the aircraft model, in order to simulate the influence of the intake effect on the lift and drag of the aircraft, an ejector system is generally designed inside the low-speed wind tunnel model of the aircraft to simulate the inlet flow of the air inlet.

[0003] In the existing injection system, after the injection high-pressure gas enters the main airflow, it will be mixed with the main airflow, and will be discharged from the exhaust outlet of the main air intake pipe together. As the pressure of the injection high-pressure air increases, the main air intake pipe will exhaust The outlet pressure increases rapidly and quickly reaches a congested state. When the ejection capacity of ...

Claims

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