Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test

A simulation test, aerothermal technology, applied in the field of high-speed aircraft aerothermal test, can solve the problems of inaccurate temperature data, accuracy and reliability problems, etc.

Inactive Publication Date: 2015-01-07
BEIHANG UNIV
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  • Application Information

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Problems solved by technology

In addition, using inaccurate temperature data to correct the cold wall heat flow data has problems with the accuracy and reliability of the results
[0007] Although the above method has certain problems, it also illustrates the necessity and difficulty of converting the cold wall heat flow boundary condition into the hot wall heat flow boundary condition in the aerothermal test simulation

Method used

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  • Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test
  • Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test
  • Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test

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specific Embodiment approach

[0031] Such as figure 1 Shown, the specific embodiment of the present invention is as follows:

[0032] 1. The metal plate is made of high-temperature-resistant nickel-based stainless steel 1Cr18Ni9Ti, with a melting point of 1450°C. This material has better anti-deformation ability at high temperatures; the thickness range of the metal sheet is 1.0-2.0mm, because it is too thick and has a large heat capacity. The response time to the changing thermal environment is long and the thermal hysteresis is serious. It is too thin and easy to deform. After testing, it is determined that it is more suitable between 1.0-2.0mm. The plane size of the metal sheet is selected as a single side length of 100mm-120mm. Since the area is not too large, the out-of-plane deformation after heating is within the available range. The ratio of the side length to the thickness of the metal sheet is between 60:1 and 120. :1, the ratio of its width to thickness is very large, so it can be approximated...

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Abstract

The invention provides a method for converting cold wall heat flux into hot wall heat flux in an aerodynamic heat simulating test. The method comprises the following steps: firstly, calculating a temperature change curve for the surface of a thin metal plate according to a cold wall heat flux boundary condition; secondly, heating the thin metal plate test piece according to the calculated temperature curve, and recording a hot wall heat flux curve for the surface of a heat flux sensor in the same plane of the thin metal plate under the temperature condition, namely by a combined method of theoretical calculation and an experimental test, finally obtaining a hot wall heat flux boundary condition which corresponds to the cold wall heat flux boundary condition and is difficultly determined by a computer. The invention provides a practicable hot wall heat flux determining method for a radiant aerodynamic heat simulating test on a high-speed aircraft.

Description

technical field [0001] The invention relates to a method for converting cold-wall heat flow into hot-wall heat flow in an aerothermal simulation test, and belongs to the field of high-speed aircraft aerodynamic heat test. Especially when using the radiation method to simulate the aerodynamic heating environment of high-speed aircraft such as missiles, the cold wall heat flow boundary conditions obtained by theoretical calculations are converted into the actual hot wall heat flow boundary conditions. Background technique [0002] Missiles, high-speed aircraft and other aircraft will have very serious "thermal barrier" problems when flying at high Mach numbers. The instantaneous heat flux density of the front end radome cone of a hypersonic vehicle flying at Mach 6 can be as high as 1.2Mw / m 2 , the stagnation temperature will exceed 1200°C. When the space shuttle passes through the atmosphere, the temperature of most areas such as the body, wings, and vertical tail is betwee...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N25/20
Inventor 吴大方王岳武杨嘉陵高镇同麦汉超
Owner BEIHANG UNIV
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