Estimation of the turbulent boundary layer pressure wavenumber-frequency spectrum using a fixed probe pair

Mathur, Gopal P.; Cannon, Mark R.

doi:10.2514/6.1990-3926

Cited by 2 publications

(2 citation statements)

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“…The panel structure then vibrates and transmit the pressure fluctuations to the interior; which is the "vibro-acoustics" part. The transmitted pressure fluctuations are responsible for the interior acoustic environment of an automobile 2,3 , the cabin of an aircraft 4,5 and the payload and crew-compartment of a space vehicle 6 . The panel vibration issue takes significance in higher Mach number flows, particularly experienced by space vehicles, which are subjected to large amplitude pressure fluctuations from flow separation and shock oscillation 7 .…”

Section: Introductionmentioning

confidence: 99%

“…For aerospace applications interest is in high speed flows where measurements of the wavenumber-frequency spectrum of pressure fluctuations are unavailable. As the Mach number increases, the convective peak of the wave number spectrum is known to strongly drive the structural modes, such as in the aircraft cabins and the payload fairings 4,5,6 . Typical flight data from space vehicles show the largest response in the transonic and low supersonic Mach number range of the flight.…”

Section: Introductionmentioning

confidence: 99%

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Wavenumber-Frequency Spectra of Pressure Fluctuations Measured via Fast Response Pressure Sensitive Paint

Panda

Roozeboom

Ross

2016

22nd AIAA/CEAS Aeroacoustics Conference

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The recent advancement in fast-response Pressure-Sensitive Paint (PSP) allows time-resolved measurements of unsteady pressure fluctuations from a dense grid of spatial points on a wind tunnel model. This capability allows for direct calculations of the wavenumber-frequency (k-ω) spectrum of pressure fluctuations. Such data, useful for the vibro-acoustics analysis of aerospace vehicles, are difficult to obtain otherwise. For the present work, time histories of pressure fluctuations on a flat plate subjected to vortex shedding from a rectangular bluff-body were measured using PSP. The light intensity levels in the photographic images were then converted to instantaneous pressure histories by applying calibration constants, which were calculated from a few dynamic pressure sensors placed at selective points on the plate. Fourier transform of the time-histories from a large number of spatial points provided k-ω spectra for pressure fluctuations. The data provides first glimpse into the possibility of creating detailed forcing functions for vibro-acoustics analysis of aerospace vehicles, albeit for a limited frequency range.

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