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.
Design and qualification of a supersonic wind tunnel for induced boundary layer transition research
2015
Article (Journal)
English
Design and qualification of a supersonic wind tunnel for induced boundary layer transition research
SAGE Publications | 2015
|Design and Qualification of a Supersonic Wind Tunnel for Transition Experiments
British Library Conference Proceedings | 2011
|British Library Online Contents | 1994
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