Experimental device for wind tunnel flow field noise assessment and assessment method

A kind of experimental device and noise technology, which is applied in the direction of measuring device, vibration measurement in fluid, aerodynamic test, etc., can solve the problem of flight test failure and achieve the effect of reducing the impact

Pending Publication Date: 2019-05-07
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0003] In recent years, in the rapid development of hypersonic vehicles, it has been found that there is a big difference between the ground wind tunnel experiment

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  • Experimental device for wind tunnel flow field noise assessment and assessment method
  • Experimental device for wind tunnel flow field noise assessment and assessment method
  • Experimental device for wind tunnel flow field noise assessment and assessment method

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Embodiment Construction

[0025] In order to make the purpose, technical solutions and advantages of the embodiments of the application clearer, the technical solutions in the embodiments of the application will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the application. Obviously, the described embodiments It is an embodiment of a part of the present application, not all of the embodiments. Based on the implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without making creative efforts belong to the scope of protection of this application.

[0026] Accordingly, the following detailed description of the embodiments of the application, provided in the accompanying drawings, is not intended to limit the scope of the claimed application, but merely represents selected embodiments of the application. Based on the implementation manners in this application, all other i...

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Abstract

The invention provides an experimental device for wind tunnel flow field noise assessment and an assessment method, and belongs to the field of experimental aerodynamics. The experimental equipment for wind tunnel flow field noise assessment includes an inlet valve, a stable section, a spraying pipe section, an experimental section and a diffusion section which communicate successively, the inletvalve is detachably connected with the stable section, the stable section is detachably connected with the spraying pipe section; and one end of the spraying pipe section extends into the experimentalsection and is detachably connected with the experimental section; and the experimental section is connected with one end of the diffusion section, the other end of the diffusion section is used forbeing connected with a vacuum tank, a control assembly is detachably installed in the stable section, and the control assembly includes a first control part for decreasing the flow field noise or a second control part for increasing the flow field noise. The experimental device further includes a first measuring probe and a second measuring probe, the first measuring probe is installed in the stable section and used for measuring the noise at anoutlet of the stable section, and the second measuring probe is installed inside the experimental section and used for measuring the noise at an outletof the spraying pipe section.

Description

technical field [0001] The present application relates to the field of experimental aerodynamics, and in particular, relates to an experimental device and an evaluation method for wind tunnel flow field noise evaluation. Background technique [0002] The wind tunnel is the main equipment for carrying out ground simulation experiments such as aircraft. The aerodynamic data of the aircraft model obtained in the wind tunnel is the basis and basis for the next step of carrying out the real aircraft flight test. Therefore, the better the quality of the wind tunnel flow field, the closer the experimental results obtained are to the real flight test, and the problems in the aircraft design can be found and solved more accurately, and the efficiency of aircraft design and the success rate of flight tests can be greatly improved. [0003] In recent years, in the rapid development of hypersonic vehicles, it has been found that there is a big difference between ground wind tunnel exper...

Claims

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Application Information

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IPC IPC(8): G01M9/00G01H3/00
Inventor 何霖陆小革
Owner NAT UNIV OF DEFENSE TECH
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