This paper presents the design and the results of the qualification test campaign of a multiple Mach number supersonic wind tunnel designed for induced boundary layer transition. Its characteristics, function, and instrumentation are described. The range of Mach numbers successfully span is presented along with the measured intensities of freestream fluctuations. All the measurement techniques implemented in the test campaigns after the qualification are introduced, and some results shown and commented to highlight their potentialities.
CitationBottini, H., Paniagua, G., Schreivogel, P., Sonda, A., De Las Heras, S.A. Design and qualification of a supersonic wind tunnel for induced boundary layer transition research. "Proceedings of the Institution of Mechanical Engineers. Part G, journal of aerospace engineering", 01 Març 2015, vol. 229, núm. 3, p. 562-578.
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