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• W2328513627 abstract "Among the many challenges that face designers of supersonic and hypersonic aircraft, the issue of boundary layer transition as it spawns from freestream disturbance receptivity is central. Experimental studies of this complex phenomenon require the characterization of acoustic disturbance sources in terms of intensity and spectral content. Among the possible sources for these studies, sparks have been identified as viable candidates, primarily because the impulsive disturbance provides broad spectrum excitation and does not suffer from wave interference issues that plague continuous sources in supersonic flow. Despite the advantages of spark sources, a number of practical issues arise in their implementation, particularly with regard to electrical noise generated by the high voltage pulse applied to the spark gap. In addition, the low static pressure levels typifying supersonic and hypersonic test sections make the implementation of any acoustic source difficult in terms of signal to noise ratio for the disturbance measurement. This work presents both experimental measurements and numerical predictions of the time-dependent sound pressure field generated by a spark discharge in air at various static pressures ranging from 90 to 3 kPa absolute. The channel generated by the spark discharge was simulated numerically using a time dependent energy source. Code validation runs were conducted using a 2-dimensional, inviscid model for a continuous harmonic point source to compare with acoustic theory, for both still air and a supersonic mean flow. The spark experiments were conducted with 5 different spark gaps to study the influence of gap spacing on sound pressure level as well. The measured data showed peak SPL's above 110 dB at the largest distance * Associate Professor, gbuck@taz.sdsmt.edu ** Graduate Student, ylime@engr.colostate.edu (3.5 inches (88.9 mm) from source) even at the lowest static pressures tested, but revealed the emergence of oscillations at low pressure, speculated to be due to reduced sensor damping under these conditions. It was also observed that the sound pressure decreased slowly with decreasing static pressure, until a threshold of about 10 kPa was reached; static pressures below this threshold resulted in substantial reductions in" @default.
• W2328513627 created "2016-06-24" @default.
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• W2328513627 date "2001-01-08" @default.
• W2328513627 modified "2023-09-24" @default.
• W2328513627 title "Numerical and experimental studies of spark-induced impulsive acoustic disturbances in compressible flow" @default.
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• W2328513627 doi "https://doi.org/10.2514/6.2001-890" @default.
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