Hypersonic velocity static wind tunnel nozzle design method and hypersonic velocity static wind tunnel nozzle transition position determining method

A hypersonic, method-determining technology, applied to measuring devices, testing of machines/structural components, instruments, etc., can solve problems such as the inconvenience of nozzles in hypersonic static wind tunnels

Active Publication Date: 2014-07-30
PEKING UNIV
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  • Claims
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Problems solved by technology

However, there is no accurate method for determining the transition position of the hypersonic static wind tunnel n

Method used

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  • Hypersonic velocity static wind tunnel nozzle design method and hypersonic velocity static wind tunnel nozzle transition position determining method
  • Hypersonic velocity static wind tunnel nozzle design method and hypersonic velocity static wind tunnel nozzle transition position determining method
  • Hypersonic velocity static wind tunnel nozzle design method and hypersonic velocity static wind tunnel nozzle transition position determining method

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Embodiment Construction

[0027] 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.

[0028] According to an embodiment of the present invention, a method for determining the transition position of a nozzle of a hypersonic static wind tunnel is provided. In order to determine the transition position of the hypersonic static wind tunnel nozzle, it is essential to understand the stability mechanism of the boundary layer and understand the reasons for the instability of the boundary layer and the change from laminar flow to turbulent flow. According to research at home and abroad, the compressible linear stability theory has been successfully applied to several different flows for transition prediction. Previous studies have shown that for supersonic nozzles with a Mach number less than 2.5, the nozzle boundary layer transition is genera...

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Abstract

The invention provides a hypersonic velocity static wind tunnel nozzle design method and a hypersonic velocity static wind tunnel nozzle transition position determining method. The hypersonic velocity static wind tunnel nozzle transition position determining method comprises the steps that a Gulet logarithm N is determined according to the design requirements of a hypersonic velocity static wind tunnel nozzle; an axle wire of the hypersonic velocity static wind tunnel nozzle serves as an X axis, and the first formula shown in the specification is utilized for determining the vertical coordinate yT of a transition point, wherein the vertical coordinate yT of a transition point conforms to a second formula shown in the specification. According to the second formula, T is the transition point, the GT is the Gulet number of the point T, deltaT is the boundary layer thickness of the point T, RdeltaT is the boundary layer thickness Reynolds number of the point T, rT is the wall curvature radius of the transition point T, y'T is the first-order derivative of the y-axis coordinate of the transition point T, and y''T is the second-order derivative of the y-axis coordinate of the transition point T; according to the vertical coordinate yT of the transition point T, the horizontal coordinate xT of the transition point T is determined. According to the hypersonic velocity static wind tunnel nozzle design method and the hypersonic velocity static wind tunnel nozzle transition position determining method, the transition position of the hypersonic velocity static wind tunnel nozzle can be easily and accurately obtained, and the repeated debugging step in the design process of the hypersonic velocity static wind tunnel nozzle is omitted.

Description

technical field [0001] The invention relates to the technical field of hypersonic wind tunnel design, and more specifically, to a method for designing a nozzle of a hypersonic static wind tunnel and a method for determining the transition position of the 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, and the experimental model 100 (see figure 1 with figure 2 shown) is fixed in the test area of ​​the pipeline, and various aerodynamic experiments are carried out according to the principle of relativity and similarity of motion to simulate various flight states in the air and obtain model experimental 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] Ordinary hypersonic wind tunnel fl...

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Application Information

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IPC IPC(8): G01M9/04
Inventor 李存标
Owner PEKING UNIV
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