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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 that the performance parameters of the experimental model cannot be known, so as to reduce the cost of wind tunnel experiment, simple structure, low cost effect

Inactive Publication Date: 2014-04-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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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 Mach numbers, and can be used for the research of aerodynamic characteristics of aircraft or air inlet schemes, so as to obtain the real performance at specific Mach numbers

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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Embodiment Construction

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

[0025] A device capable of changing the Mach number of a supersonic wind tunnel model experiment, characterized in that it includes 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 4 is installed on the su...

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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 technique capable of changing the Mach number of a supersonic wind tunnel model experiment, and belongs to the technical field of supersonic air inlets and the technical field of aerodynamic 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 adjustable airflow is generated in the pipeline by using an appropriate power device. In the experimental section, it can simulate or basically simulate the real object in the atmospheric flow field. It is used to carry out various types of aerodynamic experiments. During the experiment, the model is fixed in the test section with a pole or bracket. When the airflow blows through the model, the pressure parameters on the model are output to the measuring instrument through sensors or con...

Claims

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Application Information

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