Numerical study of shock/boundary layer interaction in supersonic overexpanded nozzles

Hadjadj, A.; Perrot, Y.; Verma, Shashi B.

doi:10.1016/j.ast.2015.01.010

Cited by 44 publications

(20 citation statements)

References 38 publications

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“…A few of these include the injection of gaseous fuel jets in a natural gas engine [1,2] or a supersonic combustor [3,4], discharge of chimney gases into the atmosphere [5,6], and thrust control of rockets and V/STOL aircraft via jets [7,8]. In most of these applications, an overall control of the fluid mechanics of the flow is required to improve the quality of the end process.…”

Section: Introductionmentioning

confidence: 99%

Flow characteristic of highly underexpanded jets from various nozzle geometries

Zhou

Yao

et al. 2017

Applied Thermal Engineering

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Section: Introductionmentioning

confidence: 99%

Flow characteristic of highly underexpanded jets from various nozzle geometries

Zhou

Yao

et al. 2017

Applied Thermal Engineering

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“…In high-speed flows in the channels the areas of interaction between the boundary layer and shock waves arise. The interaction of an inclined shock wave (oblique shock) with the boundary layer has been studied for several decades [1][2][3][4][5][6]. A strong pressure gradient caused by the impact of a shock wave on the boundary layer can lead to the flow separation.…”

Section: Introductionmentioning

confidence: 99%

Visualization of the interaction region of an oblique shock wave with a boundary layer by the radiation of a nanosecond surface sliding discharge

Mursenkova¹,

Sazonov²,

Liao³

et al. 2019

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The spatial structure of radiation of a surface sliding discharge with a duration of ~ 300 ns (plasma sheet) in inhomogeneous supersonic air flows including oblique shock wave in a discharge chamber of shock tube was experimentally investigated. The flows were created behind plane shock waves with Mach numbers 2.8-4.2; flow Mach numbers were 1.30-1.60. The flow in the discharge chamber included an oblique shock wave generated by the interaction of a supersonic flow with a small obstacle, and then reflected from the upper wall of the discharge chamber. In this case, the shock wave interacted with the boundary layer of the supersonic flow, which formed on the streamlined wall. A surface sliding discharge with a length of 100 mm and 30 mm wide was initiated on a streamlined surface at a certain moment in time. The discharge current, emission spectra, and spatial characteristics of the radiation under various conditions of discharge initiation were obtained and analyzed in experiments. The time dependence of geometry of the discharge glow region was obtained by digital processing of discharge images in flows. CFD simulation was performed to determine the shock-wave structure of the flow in the channel with an obstacle under experimental conditions. The comparison of experimental data with the results of numerical calculation of the supersonic flow field was done. It was shown that the spatial distribution of radiation from a surface sliding discharge visualizes the low density areas and the separation zone formed under the interaction of an oblique shock wave with a boundary layer.

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“…As indicated by the previous studies [3,7,11,12,34,35,[39][40][41][42], the spatial resolution in numerical modeling of supersonic flows needs to be rather high. A grid independence study by using two different meshes, i.e.…”

Section: Simulation Setupmentioning

confidence: 99%

“…A few of these include injection of gaseous fuel jets in a supersonic combustor [1][2][3], discharge of chimney gases into the atmosphere [4,5], and thrust control of rockets and V/STOL aircraft via jets [6,7]. In most of these applications, an overall control of the fluid mechanics of the flow is desirable to improve the quality of the end process.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of characteristic frequency excited highly underexpanded jets

Fan

Yao

et al. 2017

Aerospace Science and Technology

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A highly underexpanded jet with a nozzle pressure ratio of 5.60 is excited simultaneously by the inherent characteristic frequencies in the steady jet of 14.569 kHz, 37.086 kHz, and 45.695 kHz as well as other two reference frequencies of 1.0 kHz and 40.0 kHz. The flow characteristic of the excited jets is revealed by comparing to the steady jet using large eddy simulation technique. For low-frequency excitation ( f e = 1.0 kHz), the flow and acoustic fields of the forcing jet are similar with the steady jet. However, when the jet is excited by high frequencies, the acoustic source moves to the nozzle exit, and the jet potential core together with the near-field shocks oscillate periodically at the excitation frequency. The excitation at f e = 1.0 kHz increases the mixing area since y/D = 24 from the nozzle exit, which is contrary to the effect of other high frequencies that enhances the mixing in the near-field region but decreases the mixing area since y/D = 18. The peak frequency of the excited jets generally becomes identical to the excitation frequency once being excited, except the f e = 1.0 kHz and f e = 40.0 kHz jets. High-order harmonics of the dominant frequency are observed in the pressure spectrum of jets excited by high frequencies, and the dominant mode turns into the axisymmetric mode from the original helical one accordingly. In particular, forcing the jet with the axisymmetric mode of f e = 14.569 kHz provides the fewest shock cells but the largest amplitude in shock oscillation, the most harmonics in the spectrum, and the largest mixing area within 8 ≤ y/D ≤ 12.

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Numerical study of shock/boundary layer interaction in supersonic overexpanded nozzles

Cited by 44 publications

References 38 publications

Flow characteristic of highly underexpanded jets from various nozzle geometries

Flow characteristic of highly underexpanded jets from various nozzle geometries

Visualization of the interaction region of an oblique shock wave with a boundary layer by the radiation of a nanosecond surface sliding discharge

Numerical investigation of characteristic frequency excited highly underexpanded jets

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