Wind tunnel test standard model for simultaneously measuring aerodynamic force and surface heat flow

A wind tunnel test and aerodynamic technology, applied in aerodynamic tests, measuring devices, testing of machine/structural components, etc., can solve the problem of non-one-to-one correspondence of model aerodynamic surface flow state results, deviation of airflow conditions, and deviations And other issues

Pending Publication Date: 2022-01-04
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Because the wind tunnel test will be affected by various factors, the wind tunnel test of different trains will inevitably cause some small deviations in the airflow conditions, which leads to the result of the model aerodynamic force and the surface flow state results are not one-to-one correspondence, there is a deviation

Method used

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  • Wind tunnel test standard model for simultaneously measuring aerodynamic force and surface heat flow
  • Wind tunnel test standard model for simultaneously measuring aerodynamic force and surface heat flow
  • Wind tunnel test standard model for simultaneously measuring aerodynamic force and surface heat flow

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Embodiment

[0044] A wind tunnel test model that simultaneously measures aerodynamic force and surface heat flow using a balance and phosphorescence heat map technology, such as figure 1 with figure 2 As shown, it includes body 1, bullet core 2, hexagon socket head cap screw, gasket 4, sleeve 5, taper sleeve 6, balance 7, countersunk head screw 8. The bullet body is made of ceramic materials, and the thickness of the bullet body ceramic shell is 7mm. The core is made of metal materials. The shape of the core is composed of a tapered head, a small equal-diameter column section, a transition cone section, a large equal-diameter column section, and a grooved lug at the bottom (groove size: length 79mm×width 18mm × depth 4mm). Use glue that can withstand 120° high temperature to glue and fix the bullet body and bullet core. The spacer, sleeve, taper sleeve and balance are tightened and fixed by hexagon socket head screws. The sleeve includes a column of equal diameter and the bottom lug, ...

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Abstract

The invention provides a wind tunnel test standard model for simultaneously measuring aerodynamic force and surface heat flow. The wind tunnel test standard model comprises a bomb body, a bomb core, a rod-shaped threaded connecting piece, a gasket, a sleeve, a taper sleeve and a balance; the bomb core is fixed in the bomb body in a gluing mode, and the bomb core is a hollow shell mechanism with the open rear end and coaxially arranged outside the sleeve in a sleeving mode; the sleeve is of a hollow shell structure with an open rear end, the taper sleeve is installed at the front end of the balance, and the balance is stabilized in the sleeve; the gasket is placed at the front end of the sleeve, the gasket, the sleeve, the taper sleeve and the balance are sequentially fixed into a whole through the rod-shaped threaded connecting piece, and the sleeve, the taper sleeve and the balance are coaxial; a phosphorescent powder coating is uniformly sprayed on the surface of the standard model and is used for measuring heat flow distribution on the surface of the model. According to the test standard model, the model surface heat flow distribution and the model aerodynamic force result can be obtained at the same time in the hypersonic wind tunnel one-time test process, so that researchers can make model surface flow information correspond to aerodynamic force felt by the model in a wind tunnel flow field one to one.

Description

technical field [0001] The invention belongs to the technical field of high-speed wind tunnel tests, in particular to a wind tunnel test standard model for simultaneously measuring aerodynamic force and surface heat flow. Background technique [0002] In the study of the aerodynamic performance of aerospace vehicles, wind tunnel model tests and numerical calculations are the two most important research methods. In order to verify the reliability of numerical calculation results and evaluate the computational simulation ability of CFD (Computational FluidDynamics, Computational Fluid Dynamics) for various complex flow phenomena of aircraft, people usually use wind tunnel model test data for comparison and confirmation. However, wind tunnel model testing is a complex process of simulating and measuring the aerodynamic forces acting on the model in a wind tunnel. Therefore, the data of the wind tunnel model test will inevitably be affected by various factors, resulting in test...

Claims

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Application Information

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Patent Type & AuthorityApplications(China)
IPC IPC(8): G01M9/06G01M9/08
CPCG01M9/062G01M9/08
Inventor叶瑞肖翔贾广森
OwnerCHINA ACAD OF AEROSPACE AERODYNAMICS