A Flow Control Ejection System for Aircraft Model Low Speed Wind Tunnel Experiment
A wind tunnel experiment and flow control technology, applied in the testing of machines/structural components, instruments, measuring devices, etc., can solve the problems of limited intake flow, affecting the experimental effect, and congestion of the exhaust outlet of the main intake duct, etc. To achieve the effect of increasing air intake flow and improving authenticity
Active Publication Date: 2021-08-03
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology
[0004] The technical problem solved by the present invention is to provide a flow control injection system for the low-speed wind tunnel experiment of the aircraft model, which is used to solve the problem that the existing injection system is easy to cause congestion at the exhaust outlet of the main air intake pipe, and the air intake flow is limited, which affects The problem with experimental results
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[0016] A flow control injection system for aircraft model low-speed wind tunnel experiments, comprising a body 31, the inside of the body 31 is provided with a main air intake duct 13, and also includes a high-pressure nozzle support 21, a high-pressure air intake nozzle support 24, a recovery Supercharging device 25, air intake controller 28, one-way valve 26 and high-pressure gas tank 27, described main air intake pipe 13 is provided with a cylindrical cavity inside, described high-pressure air intake nozzle support 24 and high-pressure nozzle The support 21 is arranged on both sides inside the cylindrical cavity, the bottom of the high-pressure air inlet nozzle support 24 passes through the body 31 and communicates with the recovery booster 25, and the high-pressure nozzle support 21 passes through the body 31 and connects with the inlet The air controller 28 communicates, the air intake controller 28 communicates with the high-pressure gas tank 27, the one-way valve 26 comm...
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The invention discloses a flow control injection system for a low-speed wind tunnel experiment of an aircraft model. When performing a low-speed wind tunnel experiment on an aircraft model, the high-pressure air inlet nozzle recovers most of the high-pressure airflow ejected from the high-pressure nozzle, and the high-pressure airflow then enters and recovers The supercharging device pressurizes and returns to the high-pressure gas tank through the one-way valve. The main airflow and a small part of the high-pressure airflow are discharged through the outlet of the main air intake pipe. Since most of the high-pressure airflow is recovered, it no longer flows through the outlet of the main air intake pipe. It will cause congestion at the outlet of the main air intake duct, increasing the air intake flow of the main air intake duct, which can increase the simulated flow rate of the main air intake duct in the low-speed wind tunnel experiment of the aircraft model to 100% of the design flow rate, which is closer to the real working condition. Improve the realism of experiments.
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 ...
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IPC IPC(8): G01M9/06
CPCG01M9/065
Inventor 孔德英艾俊强王家启高翔
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA