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2014•Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace EngineeringOpen access

Design and qualification of a supersonic wind tunnel for induced boundary layer transition research

Henny Bottini, Guillermo Paniagua, Peter Schreivogel, Alberto Sonda, Salvador De Las Heras

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Abstract

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.

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What this paper is about

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.

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Available abstract

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.

Key concepts: Mach number, Supersonic wind tunnel, Wind tunnel, Supersonic speed, Freestream, Boundary layer, Hypersonic wind tunnel, Aerospace engineering

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