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Flow state control device and method for boundary layer of wind tunnel test

A boundary layer flow and control device technology, applied in measurement devices, aerodynamic tests, machine/structural component testing, etc., can solve problems such as the inability to meet the changes in the flow state during the test process, and the inability to adapt to wind tunnel tests.

Active Publication Date: 2018-07-20
BEIJING AEROSPACE TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

There is a certain gap between the working conditions in the wind tunnel test and the flight conditions of the aircraft. The existing design method of the forced transition device of the aircraft cannot be adapted to the wind tunnel test. In addition, due to the different requirements for the incoming flow in the wind tunnel test, the existing The forced transition device cannot meet the change of fluid state in the test process

Method used

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  • Flow state control device and method for boundary layer of wind tunnel test
  • Flow state control device and method for boundary layer of wind tunnel test
  • Flow state control device and method for boundary layer of wind tunnel test

Examples

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Effect test

Embodiment 1

[0074] The invention provides a boundary layer flow state control device for a wind tunnel test, which adopts a passive boundary layer flow state control device or a passive boundary layer flow state control device according to whether the flow state of an aircraft changes during the wind tunnel test.

[0075] The passive boundary layer flow control device is composed of a row of flow control units, and the height of the flow control is passed by k b =n b δ determined, n b is the passive height design criterion coefficient, the value range is [0.5, 1.5], where k b is the transition unit height, δ is the total enthalpy boundary layer thickness; the side length w of the flow control unit b by the formula w b =Δ b δ is determined, where Δ b is the proportional coefficient of passive side length, Δ b The value range is 0.5 to 1.5.

[0076] The active boundary layer flow state control device adopts air blowing control and consists of a row of air blowing channels, and the si...

Embodiment 2

[0078] The present invention provides as figure 2 A method for controlling the boundary layer flow state of a wind tunnel test is realized through the following steps:

[0079] 1. Determine the type of boundary layer flow regime control

[0080] The control of boundary layer flow state in wind tunnel test is passive or active, which needs to be determined according to the needs of the aircraft. If the aircraft needs to change the flow state during the wind tunnel test, the active transition control device is selected. If the aircraft only needs to maintain a flow state during the wind tunnel test and does not need to change the flow state, a passive transition control device is selected. In this example, the wind tunnel test does not need to change the flow state, so passive control is selected.

[0081] 2. Design the boundary layer flow regime control device

[0082] According to the boundary layer flow regime control type determined in step 1, a passive boundary layer f...

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Abstract

The invention provides a flow state control device and method for a boundary layer of a wind tunnel test. An active or passive boundary layer flow state control device is used according to whether theflow state of an aircraft is changed in the wind tunnel test. Thus, the flow state of the boundary layer is controlled accurately in the wind tunnel test; and different boundary-layer flow state control devices are designed according to concrete requirements for the flow state of the boundary layer in the wind tunnel test, and the flow state of the boundary layer can be controlled, and the flightstate can be simulated more accurately.

Description

technical field [0001] The invention relates to a boundary layer fluid state control device and method for a wind tunnel test, and belongs to the technical field of high-speed aircraft aerodynamic analysis. Background technique [0002] Hypersonic vehicles need to carry out ground tests in the design of structural thermal protection to check the design. At present, commonly used ground test equipment are: shock wave wind tunnel and arc wind tunnel. When a hypersonic vehicle is flying, there are two flow states in the surface boundary layer: laminar flow and turbulent flow. The difference in the surface flow state will directly affect the aerodynamic performance and thermal protection system of the aircraft. In the ground test, the surface of the test piece needs to simulate the real flow state on the surface of the aircraft. In some cases, the boundary layer flow state of the ground test cannot meet the requirements, and the boundary layer flow state needs to be controlle...

Claims

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Application Information

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IPC IPC(8): G01M9/04
Inventor 吴宁宁罗金玲朱国祥周丹康宏琳
Owner BEIJING AEROSPACE TECH INST