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Method for rapidly determining curved shock wave compression flow field air flow parameters

A bending shock wave and airflow parameter technology, applied in the direction of electrical digital data processing, special data processing applications, instruments, etc., can solve the problems of difficult application expansion, large number of calculation samples, and fitting process errors

Inactive Publication Date: 2016-05-11
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, the result depends on the type design method adopted, and the establishment process requires a large number of calculation samples, so the application is not easy to expand, and the fitting process will also bring errors

Method used

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  • Method for rapidly determining curved shock wave compression flow field air flow parameters
  • Method for rapidly determining curved shock wave compression flow field air flow parameters
  • Method for rapidly determining curved shock wave compression flow field air flow parameters

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Embodiment Construction

[0049] The present invention will be further described below in conjunction with the accompanying drawings.

[0050] Such as figure 1 shown as a figure 1 It is a schematic diagram of the original flow field, which not only contains the leading edge shock wave and compression wave, but the interaction between the two will also form a reflected wave system and a slip flow discontinuity, which will continue to interact with the downstream compression wave , which affects the flow near the wall, causing the left-handed characteristic line from the compression surface to be no longer a straight line, and the parameters such as Mach number and pressure on the characteristic line are not uniform, which is why the accurate calculation is cumbersome and difficult. The method proposed by the present invention simplifies the calculation process as follows: independently calculate the changes in the flow parameters caused by the compression wave system sent by the compression wall surfac...

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Abstract

The invention discloses a method for rapidly determining curved shock wave compression flow field air flow parameters. According to the method, change of flowing parameters caused by a compression wave system emitted by a compression wall surface and change of flowing parameters caused by an expansion wave system reflected by curved shock waves are calculated independently, in the calculation process, the compression wave system in an original flow field is simplified into Prandtl-Meyer compression waves gathered on the point S, the expansion wave system in the original flow field is simplified into an expansion wave passing through the point S, the compression wall surface parameter, the curved shock wave shape, parameters after waves, the shape of streamlines in the flow field, parameters on the streamlines and an output parameter are determined rapidly according to the simplified Prandtl-Meyer compression waves and the expansion wave. According to the method for rapidly determining curved shock wave compression flow field air flow parameters, the calculation process is simple, the calculation result can reach high precision, and the method can be used for calculating and analyzing the flow field.

Description

technical field [0001] The invention relates to a method for quickly determining airflow parameters of a supersonic or hypersonic bending shock wave compression flow field, which belongs to a method for determining airflow parameters of a flow field. Background technique [0002] The flexural shock compression flow field contains leading edge shock and isentropic compression wave. The interaction between the two will also form a reflection wave system and a slip flow discontinuity. The reflection wave system and slip flow discontinuity will continue to interact with the downstream compression wave. Therefore, the left-moving characteristic line emitted by the compression surface is generally not a straight line, and the parameters such as Mach number and pressure on the characteristic line are not uniform, which brings difficulties to the flow field analysis, and the characteristic line method is needed , finite volume method and other flow field calculation methods, which a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/00
Inventor 王磊张堃元苏纬仪金志光
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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