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Subsonic-transonic flow field ejection operating method for transient type subsonic-transonic-supersonic wind tunnel

A temporary flushing and sub-span technology, applied in the field of wind tunnel testing, can solve the problems of high front chamber pressure, excessive load, and difficulty in establishing complex model flow fields, and achieve the goals of reducing usage, expanding test capabilities, and reducing loads Effect

Active Publication Date: 2017-05-31
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art, provide a new driving mode, and solve the problems of high pressure in the antechamber and excessive load in the antechamber and difficulty in establishing a complex model flow field during the sub-span blowing test.

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  • Subsonic-transonic flow field ejection operating method for transient type subsonic-transonic-supersonic wind tunnel
  • Subsonic-transonic flow field ejection operating method for transient type subsonic-transonic-supersonic wind tunnel

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Embodiment Construction

[0022] The present invention is based on the structural characteristics of the temporary sub-span super wind tunnel. During the sub-span blowing test, especially when blowing at a high Mach number of 0.8 to 1.2, it encounters an aircraft model with a large lifting surface, in order to reduce the load and ensure the smooth completion of the experiment. , Inspired by the supersonic ram ejection driving method, a method of subsonic flow field ejection driving was created.

[0023] In view of the characteristics of the AT-1 wind tunnel, in the traditional sub-span wind tunnel test stamping drive mode, the main pressure regulating valve (12) opens slowly, while the start valve (14) can be opened quickly. When performing a blowing test, generally the main air source valve (15) is opened first, the main pressure regulating valve (12) is opened to a suitable preset position according to empirical values, and then the starting valve (14) is opened to quickly establish a flow field. In ...

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Abstract

The invention relates to a subsonic-transonic flow field ejection operating method for a transient type subsonic-transonic-supersonic wind tunnel. The method has the advantages that the subsonic-transonic flow field ejection operating manner is created on the basis of the structural features of the transient type wind tunnel to effectively lower load under the inspiration of supersonic flow field stamping ejection operation manner; the subsonic-transonic-supersonic wind tunnel usually comprises a main pressure regulating valve system, a stamping ejector system and an increment ejector system, and accordingly a blowing test has various combined operating manners; the subsonic-transonic flow field ejection operating manner is creatively used, the load can be lowered evidently, model and scale safety can be guaranteed during the subsonic-transonic blowing test and especially 0.8-1.2 high-mach-number tests, the test can be completed smoothly, and the test capacity of the wind tunnel is expanded greatly.

Description

technical field [0001] The invention relates to a method for ejection start-up in a sub-span flow field of a temporary sub-span super wind tunnel, which belongs to the field of wind tunnel tests. Background technique [0002] Wind tunnel is the most widely used tool in aerodynamic research and test, and wind tunnel test is an indispensable part of aircraft development. AT-1 wind tunnel is a typical temporary sub-span super wind tunnel, its structure is as attached figure 1 As shown, it includes main pipeline (1), damping filter screen (2), front chamber (3), nozzle pipe (4), test section (5), supersonic diffusion section (6), suction ejector (7) , subsonic diffusion section (8), exhaust throttle valve (9), incremental ejector (10), ejector pressure regulating valve (11), main pressure regulating valve (12), bypass valve (13 ), starting valve (14), air source main valve (15), air source (16), silencer tower (17). Normally, when the sub-span Mach number is 0.4 to 1.2, the t...

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Application Information

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IPC IPC(8): G01M9/02
CPCG01M9/02
Inventor 侯逸青王复春宋法振赵睿
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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