Supersonic wind tunnel and its determination method

A method to determine the supersonic velocity, applied in the direction of measuring devices, instruments, aerodynamic tests, etc., can solve problems such as excessive reflected light, achieve the effect of improving the quality of the flow field, ensuring uniformity, and reducing interference

Active Publication Date: 2016-05-04
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0005] The present invention aims to provide a supersonic wind tunnel and its determination method to solve the problem of excessively strong reflected light caused by sheet light in the optical measurement of supersonic wind tunnels with two-dimensional or axisymmetric configurations in the prior art

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  • Supersonic wind tunnel and its determination method
  • Supersonic wind tunnel and its determination method
  • Supersonic wind tunnel and its determination method

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Embodiment Construction

[0032] Hereinafter, the present invention will be described in detail with reference to the drawings and examples. It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other.

[0033] Such as Figures 1 to 9 As shown, according to an embodiment of the present invention, the supersonic wind tunnel includes: a stabilizing section 40 for rectifying the airflow; a nozzle 10 connected downstream of the stabilizing section 40, and the cross-sectional shape of the outlet of the nozzle 10 is the first Polygon, at least one of the two included angles formed by any side of the first polygon and the adjacent two sides is not equal to 90 degrees; the test section 20 is connected to the downstream of the nozzle 10, and the inlet end of the test section 20 is connected to the The outlet end of the nozzle 10 matches.

[0034] The inlet end of the test section 20 has the same cross-secti...

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Abstract

The invention provides an ultrasonic wind tunnel and a determining method thereof. The ultrasonic wind tunnel comprises a stable section (40), a spray pipe (10) and a test section (20), wherein the stable section is used for rectifying airflow; the spray pipe is connected to the downstream of the stable section (40), the cross section of an outlet of the spray pipe (10) is in a first polygonal shape, and at least one of two angles formed by any edge and two adjacent edges of the first polygon is not equal to 90 degrees; the test section (20) is connected to the downstream of the spray pipe (10), and an inlet end of the test section (20) is matched with an outlet end of the spray pipe (10). Multiple observation points can be provided through the test section of the first polygon, and all-around observation can be provided, so that the experimental precision can be improved.

Description

technical field [0001] The invention relates to aerodynamic equipment, in particular to a supersonic wind tunnel and a determination method thereof. Background technique [0002] A supersonic wind tunnel generally consists of a transition section, a stabilization section, a nozzle section, a test section, a diffuser section, and a driving device. Different schemes have different structural forms and different laboratory layouts. Manufacture, installation, and performance all have a major impact. [0003] The literature "Wind Tunnel Design Principles, Wu Ronglin, 1985" and "High and Low Speed ​​Wind Tunnel Startup and Structural Design, Liu Zhengchong, 2003" introduced the design principles and design process of supersonic wind tunnels in detail. The doctoral dissertation of the National University of Defense Technology "Experimental Research on the Space-Time Structure of Supersonic Mixed Layers, Zhao Yuxin, 2008" designed a supersonic mixing wind tunnel mainly composed of ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/02
Inventor 赵玉新马志成王振国
Owner NAT UNIV OF DEFENSE TECH
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