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Method for expanding silent test area of hypersonic-velocity silent spray pipe and hypersonic-velocity spray pipe

A technology of hypersonic speed and test area, which is applied in aerodynamic test, machine/structural component test, instrument, etc. It can solve the problem of small test area and achieve the effect of improving applicability, extending length and expanding test area

Active Publication Date: 2014-07-30
PEKING UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The present invention aims to provide a method for expanding the static test area of ​​a hypersonic silent nozzle and a hypersonic nozzle to solve the problem that the test area of ​​a hypersonic silent nozzle in the prior art is relatively small

Method used

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  • Method for expanding silent test area of hypersonic-velocity silent spray pipe and hypersonic-velocity spray pipe
  • Method for expanding silent test area of hypersonic-velocity silent spray pipe and hypersonic-velocity spray pipe
  • Method for expanding silent test area of hypersonic-velocity silent spray pipe and hypersonic-velocity spray pipe

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Embodiment Construction

[0027] 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.

[0028] Such as Figures 1 to 3 As shown, according to the embodiment of the present invention, the method for expanding the static test area of ​​the hypersonic silent nozzle includes: determining the transition position T of the nozzle; determining the position of the first suction hole 10, the first suction hole 10 runs through the nozzle The pipe wall, and the first suction hole 10 intersects with the inner wall of the nozzle to form a first intersection, and the transition position T is located in the first intersection; determine the axis between the first suction hole 10 and the axis of the nozzle Angle α between; determine the cross-sectional shape of the first suction hole 10, and determine ...

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Abstract

The invention provides a method for expanding a silent test area of a hypersonic-velocity silent spray pipe and the hypersonic-velocity spray pipe. The method for expanding the silent test area of the hypersonic-velocity silent spray pipe includes the steps that a transition position T of the spray pipe is determined; the position of a first suction hole is determined, the first suction hole penetrates through the pipe wall of the spray pipe, the first suction hole and the inner wall face of the spray pipe intersect to form a first intersection face, and the transition position T is located in the first intersection face; the included angle alpha between the axis of the first suction hole and the axis of the spray pipe is determined; the shape of the cross section of the first suction hole is determined, and the sectional area of the first suction hole is determined. Through the method for expanding the silent test area of the hypersonic-velocity silent spray pipe, the silent test area of the hypersonic-velocity silent spray pipe can be expanded.

Description

technical field [0001] The invention relates to aerodynamic experimental equipment, in particular to a method for expanding the static test area of ​​a hypersonic silent nozzle and the hypersonic nozzle. Background technique [0002] The wind tunnel experiment refers to using a power device to drive a controllable airflow in a pipeline designed according to certain requirements, fixing the experimental model in the test area of ​​the pipeline, and performing various air tests according to the principle of relativity and similarity of motion. Dynamic experiments to simulate various flight states in the air and obtain model experiment data. Hypersonic wind tunnel is a kind of wind tunnel, which is widely used in model experiments of missiles, aircraft, rockets, etc. It is a basic experimental equipment in the field of aerospace. [0003] The existing hypersonic wind tunnel flow field has relatively high aerodynamic noise and turbulence, which is 1 to 2 orders of magnitude hig...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/02G01M9/04
Inventor 李存标
Owner PEKING UNIV
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