In-Flight Visualization of Supersonic Flow Transition Using Infrared Imaging

C. P. van Dam; H. J. Shiju; D. W. Banks; R. R. Tracy; J. Chase

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In-Flight Visualization of Supersonic Flow Transition Using Infrared Imaging

机译：使用红外成像对超音速流动过渡进行飞行可视化

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Infrared visualization was used to obtain information on the state of the boundary layer of a natural laminar flow airfoil in supersonic flight. In addition to the laminar/turbulent transition boundary, the infrared camera was able to detect shock waves and present a time-dependent view of the flow field. Thermal and flow mechanisms on the surface in flight were modeled numerically to aid in the design of the flight experiment and facilitate analysis of recorded infrared footage. A commercially available infrared camera was adapted for airborne use in this application. Readily available infrared technology has the capability to provide detailed visualization of various flow phenomena in subsonic to hypersonic flight regimes.

机译：红外可视化用于获得超音速飞行中自然层流翼型边界层状态的信息。除了层流/湍流过渡边界外，红外热像仪还能够检测到冲击波，并提供与时间有关的流场视图。对飞行表面上的热和流动机制进行了数值建模，以帮助设计飞行实验并有助于分析记录的红外镜头。市售的红外热像仪适用于此应用中的机载使用。现成的红外技术具有提供亚音速到高音速飞行状态下各种流动现象的详细可视化的能力。

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来源
《Journal of Aircraft》 |2002年第6期|p.936-944|共9页
作者
C. P. van Dam; H. J. Shiju; D. W. Banks; R. R. Tracy; J. Chase;
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作者单位

University of California, Davis, California 95616;

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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
中图分类航空;
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In-Flight Visualization of Supersonic Flow Transition Using Infrared Imaging

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