Ultrasonic-velocity free vortex wind tunnel

A supersonic, free technology, applied in the field of wind tunnels, which can solve the problems of inability to directly expand the free vortex wind tunnel, poor optical test environment, and difficulty in observing the boundary layer inside the nozzle.

Active Publication Date: 2011-02-16
NAT UNIV OF DEFENSE TECH
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  • Application Information

AI Technical Summary

Problems solved by technology

[0011] The existing technology mainly emphasizes the profile design of the free vortex nozzle and the design of the free vortex aerodynamic window, which cannot be directly extended to the design of the free vortex wind tunnel
[0012] The existing wind tunnel design technology still has some shortcomings for the study of supersonic flow mechani

Method used

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  • Ultrasonic-velocity free vortex wind tunnel
  • Ultrasonic-velocity free vortex wind tunnel

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Embodiment Construction

[0032] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways defined and covered by the claims.

[0033] The outer peripheral wall referred to in this paper refers to the peripheral wall located farther from the position of the center of the free vortex in the wind tunnel structure, and the inner peripheral wall refers to the peripheral wall located closer to the position of the free vortex center in the wind tunnel structure. the surrounding wall.

[0034] Such as figure 1 As shown, the supersonic free vortex wind tunnel according to the present invention includes: a front transition section 1, which is used to introduce airflow, and perform a first-stage rectification on the airflow, and pass the external airflow with irregular flow through the front transition section 1 to form The airflow with certain flow characteristics is ready for it to...

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Abstract

The invention provides an ultrasonic-velocity free vortex wind tunnel, comprising a transition section (1), a stabile section (2) and a spray pipe experiment section (3), wherein the transition section (1) is used for importing airflow and carrying out primary rectification to the airflow; the stable section (2) is connected with the downstream of the transition section (1) and used for carrying out secondary rectification to the airflow; and the spray pipe experiment section (3) is connected with the downstream of the stable section (2), a transparent window is formed on the peripheral wall of the spray pipe experiment section (3), and the spray pipe experiment section (3) comprises a spray pipe part (31) constructed into a free vortex spray pipe structure for accelerating the airflow to an ultrasonic-velocity free vortex state and an experiment part (32) arranged at the downstream of the spray pipe part (31) and used for ensuring that the velocity field of the airflow at the inlet of a wind hole experiment part satisfies the ultrasonic-velocity free vortex distribution so as to obtain ideal ultrasonic-velocity free vortex in the wind hole.

Description

technical field [0001] The invention relates to a wind tunnel, in particular to a supersonic free vortex wind tunnel. Background technique [0002] With the development of modern aerodynamic technology, the study of aerodynamic mechanism is becoming more and more important. As a typical compressible flow affected by the curvature of the flow direction, the study of supersonic free vortex not only has a wide application background but also has important theoretical significance. [0003] The supersonic free vortex velocity field satisfies the free vortex distribution, that is, the product of the flow velocity and the radius of curvature of the streamline is constant. Due to the high flow velocity, the flow field has unsteady and multi-scale characteristics. Quantitative flow imaging technology is an important means to study these characteristics. It requires a free vortex wind tunnel with a good optical measurement environment, and the corresponding wind tunnel optical window...

Claims

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Application Information

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IPC IPC(8): G01M9/04G01M9/02
Inventor 赵玉新王振国刘卫东梁剑寒
Owner NAT UNIV OF DEFENSE TECH
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