On boundary layer transition in high-subsonic and transonic flow under the influence of acoustic disturbances and free-stream turbulence

Murthy, Sreedhara V.; Steinle, Frank W.

doi:10.2514/6.1985-82

Cited by 3 publications

(1 citation statement)

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“…3,4 Experiments in natural boundary layer transition require a facility that interferes as less as possible with the transition process. At the supersonic Mach numbers, for instance, the facility must not produce strong pressure fluctuations, namely, their RMS should be less than about 1% of p ∞ , 5 and the velocity fluctuations should be bounded. 6 If not so, the influence of p and u on the transition process would hinder the extrapolation of the experimental results to real-flight conditions.…”

Section: Introductionmentioning

confidence: 99%

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

Bottini

Paniagua

Schreivogel

et al. 2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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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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Section: Introductionmentioning

confidence: 99%