Prediction of fluctuating pressure in attached and separated compressible flow

Laganelli, A. L.; Wolfe, H. F.; Wentz, Kenneth R.

doi:10.2514/6.1993-286

Cited by 4 publications

(5 citation statements)

References 10 publications

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“…Laganelli and Wolfe [7] proposed a model based on Robertson's work [24] that takes into account viscous effects, compressibility and heat transfer of the medium. Both experimental data and fluid dynamics principles of attached zero-pressure gradient and separated turbulent boundary layer flows were taken into account during the development of this model.…”

Section: Laganelli and Wolfe -1989mentioning

confidence: 99%

“…Various WPSM have been developed based on experimental measurements, theoretical analysis and numerical simulations. Past studies have focused on low speed flows with the compressibility effects neglected [1,2,3], or weak compressibility effects were taken into account [4,5,6,7]. More recent papers have introduced the effects of favourable and adverse pressure gradient [8,9] without considering high-speed compressible flows.…”

Section: Introductionmentioning

confidence: 99%

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Wall-pressure spectra models for supersonic and hypersonic turbulent boundary layers

Ritos

Drikakis

Kokkinakis

2019

Journal of Sound and Vibration

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This paper presents an investigation of pressure fluctuations spectra beneath supersonic and hypersonic turbulent boundary layers at zero pressure gradient. High-order implicit Large Eddy Simulations have been used to provide numerical data for assessing existing models and further improving their qualitative accuracy in predicting wall-pressure spectra. Several different models have been investigated and it is shown that existing models fail to capture the correct behaviour of pressure fluctuations in supersonic and hypersonic boundary layers across a broad range of frequencies. The models have been modified by introducing compressibility corrections. The modified models are validated against implicit Large Eddy Simulations, Direct Numerical Simulations, and experimental data. The qualitative accuracy of the models is discussed and the most promising model is identified.

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Section: Laganelli and Wolfe -1989mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Wall-pressure spectra models for supersonic and hypersonic turbulent boundary layers

Ritos

Drikakis

Kokkinakis

2019

Journal of Sound and Vibration

View full text Add to dashboard Cite

show abstract

“…This low frequency range is known to represent the dominant oscillation frequency of the separation shock foot [1]. This frequency range also corresponds to the range in which aerostructures and aeroshells typically have resonant frequencies that can lead to highcycle fatigue, also known as sonic fatigue, due to severe aero-acoustic and mechanical vibration loading [6]. As such, impinging shocks can have disastrous effects due to the huge low frequency fluctuating loads they impart on aircraft.…”

Section: Introduction 11 Shock Boundary Layer Interactionsmentioning

confidence: 99%

“…6 shows an experimental configuration of the rubber-insert model with the 20°c ompression ramp mounted. The 24°ramp face is on the opposite end of the ramp block, and the compression ramp angles were varied between test cases and not actively during the experiment.…”

mentioning

confidence: 99%

“…6 shows the top-down view surface streakline visualization comparison between the acrylic-insert and rubber-insert models for the same 16°compression ramp SBLI. The top half of the frame corresponds to the SBLI over the compliant, rubberinsert model as it did inFigure 3.5, however, the bottom half of the frame now corresponds to the SBLI over the rigid, acrylic model.…”

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confidence: 99%

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