高超声速风洞压敏漆试验技术

doi:10.7527/S1000-6893.2017.120890

Abstract

Abstract:

Some key technological problems and their solutions for pressure sensitive paint (PSP) testing in the hypersonic wind tunnel are discussed. The self-designed PSP calibration and measurement systems are used to examine the performances of EC-PSP, including applicability of the material in the hypersonic flow condition, function of image processing software, and feasibility of data processing method at high temperature. Based on the compression corner flow, hypersonic wind tunnel test at Mach number 5 are carried out to validate the PSP testing technique, and auxiliary means of infrared temperature-measuring is employed to acquire the temperature distribution on the model surface. The results show that based on the changes of the pressure on the surface of the compression corner model, the flow characteristics can be obtained with high-order accuracy, and continuous pressure distributions can be consequently obtained.

Key words: hypersonic, wind tunnel, pressure sensitive paint (PSP), compression corner, image processing

CLC Number:

V211.74

LIN Jingzhou, XIE Futian, ZHONG Jun, CHEN Lei, CHEN Liusheng. Pressure sensitive paint test technique in hypersonic wind tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(7): 120890-120890.

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Pressure sensitive paint test technique in hypersonic wind tunnel

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