High-enthalpy shock tunnel total temperature measurement method

A shock wave wind tunnel and measurement method technology, applied in the field of wind tunnel test, can solve the problem that the air velocity, pressure, temperature and composition cannot be measured in the wind tunnel, the ball head heat flow calibration method cannot be used, and the expansion wave interference cannot be reflected. effects, etc.

Active Publication Date: 2020-12-11
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

Due to the obvious attenuation of the shock wave in the shock tube, and the limitation of the number of pressure sensors and the space at the end of the shock tube, this method of estimating the total temperature based on the shock wave velocity has a large error, and does not change with time, so it cannot reflect the expansion. Interference effects such as waves
Another method is to calculate the total temperature through the heat flow of the ball head, which also has a large error. On the one hand, due to

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[0051] In order to better understand the above technical solutions, the technical solutions of the present application will be described in detail below through the accompanying drawings and specific examples. It should be understood that the embodiments of the present application and the specific features in the examples are detailed descriptions of the technical solutions of the present application, and It is not a limitation to the technical solutions of the present application, and the embodiments of the present application and the technical features in the embodiments can be combined without conflict.

[0052] The method for measuring the total temperature in a high-enthalpy shock tunnel provided by the embodiment of the present application will be described in further detail below in conjunction with the accompanying drawings. The specific implementation methods may include (such as figure 1 , 2 shown): Firstly, the sound velocity of the gas in the high-enthalpy shock tu...

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Abstract

The invention discloses a high-enthalpy shock tunnel total temperature measurement method and belongs to the technical field of wind tunnel tests. According to the invention, the sound velocity of theplenum gas is measured through the photoinduced transient grating spectrum technology, and then the temperature, namely the total temperature, of the plenum gas of the high-enthalpy shock tunnel is calculated through numerical iteration according to the plenum gas pressure of the high-enthalpy shock tunnel and the chemical equilibrium theory.

Description

technical field [0001] The invention relates to a method for measuring total temperature in a high-enthalpy shock wave wind tunnel, belonging to the technical field of wind tunnel tests. Background technique [0002] High-enthalpy shock tunnels have been widely used in the research of high-temperature gas effects and high-Mach number scramjet engines, but are affected by high-temperature gas effects, that is, the molecular vibrations and Physical and chemical phenomena such as air dissociation and ionization lead to large changes in the composition and thermodynamic parameters of the test gas, making it difficult to accurately determine the simulation parameters, especially the total temperature can only be estimated by indirect means. [0003] At present, there are two methods for obtaining the total temperature in shock tunnel simulation. One is to obtain the movement velocity of the shock wave in the shock tube by measuring the pressure change along the wall surface of t...

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Application Information

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IPC IPC(8): G01M9/06
CPCG01M9/06Y02T90/00
Inventor 卢洪波陈星江海南文帅林键谌君谋
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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