Device for changing Mach number in supersonic velocity wind tunnel model experiment and working method

A model experiment, Mach number technology, applied in the direction of measuring device, aerodynamic test, machine/structural component test, etc., can solve the problem of not being able to know the performance parameters of the experimental model, so as to reduce the cost of wind tunnel experiments, facilitate processing, low cost effect

Inactive Publication Date: 2012-07-25
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

The present invention can solve the problem that the current supersonic wind tunnel cannot obtain the performance parameters of the experimental model at certain specific M

Method used

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  • Device for changing Mach number in supersonic velocity wind tunnel model experiment and working method
  • Device for changing Mach number in supersonic velocity wind tunnel model experiment and working method
  • Device for changing Mach number in supersonic velocity wind tunnel model experiment and working method

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Example Embodiment

[0024] The present invention will be described more fully below with reference to the accompanying drawings. What is shown in each figure is an application example of the present invention, and it should not be interpreted that the present invention is only limited to the application examples described herein. The experimental model given in the figure is an airplane inlet model, excluding the rear fuselage and wings of the airplane. It is also applicable to other supersonic aircraft models such as full-aircraft models and individual inlet models. This application example is an airplane air inlet experiment, and the present invention can also be implemented for an airplane outflow experiment.

[0025] A device capable of changing the Mach number of the supersonic wind tunnel model experiment, which is characterized by comprising a shock plate 2, an experimental model 4, a wind tunnel support member composed of a supporting base 6 and a wind tunnel support 7; the experimental model...

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Abstract

The invention discloses a device for changing Mach number in a supersonic velocity wind tunnel model experiment and a working method, which relate to the technical field of supersonic velocity wind tunnel experiments. The invention comprises an experiment model and a wind tunnel support element. The wind tunnel support element comprises a support base and a wind tunnel support. The experiment model is fixed on the wind tunnel support through the support base. The wind tunnel support element further comprises a shock wave plate fixed on the wind tunnel support element. The device for changing the Mach number in the supersonic velocity wind tunnel model experiment solves the problem that the model experiment at certain Mach numbers cannot be performed by the supersonic velocity wind tunnel and avoids the problem that parameter interpolation brings errors under two experimental states where the Mach numbers are more than or less than the set Mach number, so that the actual aerodynamic performance of the experiment model at a special Mach number can be obtained and half of the cost for the wind tunnel experiment is reduced.

Description

Technical field [0001] The invention relates to an experimental technology capable of changing the Mach number of supersonic wind tunnel model experiments, and belongs to the technical field of supersonic inlet ducts and the technical field of aerodynamics experiments. Background technique [0002] The wind tunnel is the main equipment for aerodynamic experiments. The so-called wind tunnel is a kind of pipeline specially designed according to certain requirements. In this special pipeline, an appropriate power device is used to generate adjustable airflow in the pipeline. The experimental section can simulate or basically simulate the physical object in the large airflow field. Circumstances, used to conduct various types of aerodynamic experiments. During the experiment, the model is fixed in the experimental section with a support rod or bracket. When the airflow blows through the model, the pressure parameters on the model are output to the measuring instrument through the se...

Claims

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Application Information

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IPC IPC(8): G01M9/08G01M9/02
Inventor 李博郭荣伟李航
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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