Hypersonic velocity spray pipe structure
A hypersonic and nozzle technology, applied in the field of wind tunnel experiments, can solve the problems of poor quality of the nozzle air flow field, achieve the effects of improving performance and flow field quality, reducing turbulence and noise, and improving reliability
Inactive Publication Date: 2015-01-21
NAT UNIV OF DEFENSE TECH
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Problems solved by technology
[0007] The purpose of the present invention is to provide a hypersonic nozzle structure to solve the technical problem of poor quality of the air flow field in the nozzle in the existing wind tunnel experiments
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[0036] 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 various ways defined and covered by the claims.
[0037] In the present invention, one or more suction grooves are arranged on the throat of the traditional nozzle to "break" the position of the throat, so that the curve of the nozzle at the throat is no longer continuous. In the present invention, a suction groove is arranged between the constriction part and the expansion part to suck out the turbulent boundary layer developed along the constriction wall surface of the nozzle, thereby eliminating the influence of turbulence on the downstream section of the nozzle to maintain the wall surface of the nozzle The boundary layer is laminar flow, which improves the flow field quality and performance of the nozzle, and is conducive to greatly reducing the turbulence and noise of the nozzle.
[0038] see figu...
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The invention discloses a hypersonic velocity spray pipe structure. The hypersonic velocity spray pipe structure comprises a contraction portion located at the upper stream of the spray pipe, an expansion portion located at the down stream of the spray pipe and a throat portion for linking up the contraction portion with the expansion portion, wherein a pumping groove for improving the quality of an airflow filed in the spray pipe is arranged on the throat portion and pumps out a turbulent boundary layer which is in the spray pipe and develops along a contraction wall face. According to the hypersonic velocity spray pipe structure, the contraction portion and the throat portion are enabled to be discontinuous by arranging the pumping groove on the throat portion of a traditional spray pipe, the turbulent boundary layer developing along the contraction wall face of the spray pipe is pumped out with the aid of the pumping groove, influences of turbulent flow to the down stream section of the spray pipe are eliminated, the properties of the spray pipe and the flow field quality can be improved and turbulivity and noise of the spray pipe can be reduced drastically by using a wall face boundary layer supporting the spray pipe as laminar flow, so that the reliability of hypersonic velocity wind tunnel test data is improved.
Description
technical field [0001] The invention relates to the field of wind tunnel experiments, in particular to a nozzle design applied to hypersonic wind tunnel experiments. Background technique [0002] The wind tunnel experiment is based on the relative principle of motion, fixing the model or object in the artificial environment on the ground, artificially creating airflow to simulate various flight states in the air, and obtaining experimental data. Hypersonic wind tunnels are widely used in model experiments of missiles, hypersonic vehicles, artificial satellites, space shuttles, and aerospace aircraft. They are very important aerodynamic ground experimental equipment in the aerospace field. [0003] The nozzle is a key component of the hypersonic wind tunnel, which is installed upstream of the experimental section of the wind tunnel for the purpose of generating hypersonic airflow in the experimental section. The working process of the nozzle is as follows: first, the gas flo...
Claims
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IPC IPC(8): G01M9/04
Inventor 周勇为易仕和
Owner NAT UNIV OF DEFENSE TECH