Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Method for calculating hypersonic wind tunnel axisymmetric nozzle inner profile

An axisymmetric nozzle and hypersonic technology, applied in the field of fluid mechanics, can solve the problems of flow disturbance, discontinuity, and curvature radius discontinuity in the test section

Active Publication Date: 2020-10-30
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
View PDF6 Cites 11 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in such a nozzle, the Mach number gradient along the axial direction is discontinuous at point B, and its curvature radius is discontinuous at the inflection point. In theory, the curvature discontinuity will cause the boundary layer of the nozzle to is negative; if the curvature is continuous, the growth of the boundary layer is smooth, and even if the growth of the boundary layer is calculated accurately, the viscosity correction of the nozzle profile is only for the design operating conditions, then the correction amount It can only be applied to the non-viscous shape under the operating conditions of the meter, so the deviation of the growth of the boundary layer will produce discontinuities when the operating conditions are deviated from the design, and these discontinuities will follow the rough part of the nozzle due to machining. movement, causing disturbances in the flow in the test section

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Method for calculating hypersonic wind tunnel axisymmetric nozzle inner profile
  • Method for calculating hypersonic wind tunnel axisymmetric nozzle inner profile
  • Method for calculating hypersonic wind tunnel axisymmetric nozzle inner profile

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0239] The present invention will be further described in detail below in conjunction with the accompanying drawings, so that those skilled in the art can implement it with reference to the description.

[0240] It should be understood that terms such as "having", "comprising" and "including" as used herein do not entail the presence or addition of one or more other elements or combinations thereof.

[0241] Such as Figure 1-6 Shown: a method for calculating the inner profile of a hypersonic wind tunnel axisymmetric nozzle of the present invention, comprising the following steps:

[0242] Step 1. Given the initial condition parameters of the inner surface, use the initial condition parameters to calculate the inner surface of the axisymmetric nozzle; the calculation of the inner surface of the axisymmetric nozzle mainly includes the calculation of the potential flow surface and the correction of the boundary layer of the supersonic potential flow surface ; Among them, the po...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention discloses a method for calculating an inner profile of an axisymmetric nozzle of a hypersonic wind tunnel. The method comprises the following steps: 1, giving initial condition parameters; 2, calculating subsonic velocity profile coordinates of the axisymmetric nozzle; 3, calculating supersonic velocity profile coordinates of the axisymmetric nozzle, including the steps: calculatingthroat area profile parameters, calculating wave-front airflow parameters along the radial direction, calculating Mach number distribution on the center line of the conversion area, calculating parameters of a wave absorbing area, calculating a molded surface by utilizing an axisymmetric characteristic line grid, and calculating wall surface coordinates of the axisymmetric nozzle; 4, carrying outcorrection calculation on the boundary layer of the supersonic velocity section bit flow profile of the axisymmetric nozzle. According to the nozzle profile designed through the method, Mach numbers needed by flow fields are consistent, Mach number distribution of a nozzle outlet is uniform, MATLAB software programming can be conveniently adopted for achieving, the profile coordinates can be rapidly obtained, and the universality is achieved when the axisymmetric nozzle profile is calculated.

Description

technical field [0001] The invention belongs to the technical field of fluid mechanics, and more specifically, the invention relates to a method for calculating the inner profile of an axisymmetric nozzle of a hypersonic wind tunnel. Background technique [0002] The aerodynamic design of the axisymmetric nozzle mainly includes two parts: potential flow profile (subsonic section and supersonic section) and supersonic potential flow surface boundary layer correction. The potential flow is further divided into three regions: the first region is the subsonic region; the second region is the throat region from the throat to the inflection point; the third region is the transition region from the inflection point to the exit of the nozzle. [0003] In the throat, the shape is given by a monotonically increasing cubic curve. In the transition region, the shape is mainly calculated by the Cresci method, such as figure 1 As shown, it is assumed that the flow starts from the source...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/13G06F30/17G06F30/23G06F30/28G06F113/08G06F119/14
CPCG06F30/13G06F30/17G06F30/23G06F30/28G06F2113/08G06F2119/14Y02T90/00
Inventor 黄飓杨永能胥继斌付泰杨海滨张伟张长丰蒲麒刘奇王晓宇贾霜张利波
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products