Abstract
Pressure-sensitive paint measurement can obtain a much more detailed surface pressure distribution than can be obtained using conventional pressure taps. However, the pressure-sensitive paint has effect of self-illumination and it is sensitive not only to pressure but also to temperature, and where high accuracy is required, it is essential to compensate for these self-illumination and temperature-dependency. This paper discusses data processing methods for pressure-sensitive paint measurement in transonic industrial wind tunnel testing, including the outline of its measurement system. As the result, detailed pressure measurement for development of airplane is described, and the efficacy of self-illumination correction is evaluated.
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