Experimental Investigation into the Turbulence Flowfield of In-Flight Round Jets

Proenca, Anderson; Lawrence, Jack; Self, Rod H.

doi:10.2514/1.j059035

Cited by 14 publications

(18 citation statements)

References 23 publications

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“…The flight nozzle-exhaust diameter is 300 mm and is capable of producing steady flows up to . Further information about the Doak Laboratory facility and the FJR can be found in Proença, Lawrence & Self (2020 a ).…”

Section: Experimental Set-upmentioning

confidence: 99%

An experimental investigation into model-scale installed jet–pylon–wing noise

et al. 2021

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A model-scale experimental investigation of an installed jet–pylon–wing configuration was conducted at the University of Southampton, with the scope to study the effect a pylon has on noise generation and to clarify its impact on the fluctuating wall-pressure load. The set-up consisted of two single-stream nozzles, a baseline axisymmetric annular nozzle and a partially blocked annular pylon nozzle. The nozzles were tested first isolated and then installed next to a NACA4415 aerofoil ‘wing’ at a single nozzle–wing position. The jet Mach number was varied between $0.5 \leq M_{{j}} \leq 0.8$ and measurements were performed both under static and in-flight ambient flow conditions up to ${M_{{f}} = 0.2}$ . The jet flow-field qualification was carried out using a single-velocity-component hot-wire anemometer probe. The pressure field on the wing surface was investigated using two miniature wall-pressure transducers that were flush-mounted in the streamwise and spanwise directions within the pressure side of the wing. A linear ‘flyover’ microphone array was used to record the noise radiated to the far field. The unsteady pressure data were analysed in both time and frequency domains using multi-variate statistics, highlighting a far-field noise reduction provided by the presence of the pylon only in the installed case. Furthermore, the wake field generated behind the pylon is seen to significantly modify the wall-pressure fluctuations, particularly at streamwise locations close to the pylon trailing edge.

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Section: Experimental Set-upmentioning

confidence: 99%

An experimental investigation into model-scale installed jet–pylon–wing noise

et al. 2021

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“…The simulation results were validated against experimental data obtained at the Doak Laboratory Flight Jet Rig [45], located at the University of Southampton. In general, the near-field flow statistics obtained from the simulation were found to agree well with those obtained from experiments.…”

Section: Discussionmentioning

confidence: 99%

“…6. Further information about the Doak Laboratory, the FJR, and the flight and core jet nozzles can be found in reference [45].…”

Section: A Facility and Hardwarementioning

confidence: 99%

“…The purpose of this paper is to further explore the capabilities of the DG method in the context of jet aeroacoustics. To this end, results obtained with the compressible flow solver implemented in the Nektar++ spectral/hp element framework [41][42][43][44] are compared against experimental data obtained at the Doak Laboratory Flight Jet Rig (FJR) [45], located at the University of Southampton. The FJR is designed to incorporate the effects of a flight stream.…”

Section: Introductionmentioning

confidence: 99%

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Aeroacoustic Analysis of a Subsonic Jet using the Discontinuous Galerkin Method

Lindblad

Sherwin

Cantwell

et al. 2022

28th AIAA/CEAS Aeroacoustics 2022 Conference

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In this work, the open-source spectral/hp element framework Nektar++ (www.nektar.info) is coupled with the Antares library (www.cerfacs.fr/antares/) to predict noise from a subsonic jet. Nektar++ uses the high-order discontinuous Galerkin method to solve the compressible Navier-Stokes equations on unstructured grids. Unresolved turbulent scales are modeled using an implicit Large Eddy Simulation approach. In this approach, the favourable dissipation properties of the discontinuous Galerkin method are used to remove the highest resolved wavenumbers from the solution. For time-integration, an implicit, matrix-free, Newton-Krylov method is used. To compute the far-field noise, Antares solves the Ffowcs Williams -Hawkings equation for a permeable integration surface in the time-domain using a source-time dominant algorithm. The simulation results are validated against experimental data obtained in the Doak Laboratory Flight Jet Rig, located at the University of Southampton.

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“…Each test point was recorded for 10 seconds at a sampling rate of 200,000 samples per second. Additional information about the experimental facility, instrumentation, and acquisition systems can be found in the literature [10,11].…”

Section: Experimental Methodologymentioning

confidence: 99%

Far-field pressure measurements of elliptic jets discharged close to a wing

Proenca

Lawrence

2022

IOP Conf. Ser.: Mater. Sci. Eng.

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This paper presents a preliminary experimental investigation into the acoustics of two elliptical jet nozzles installed close to a wing model. Acoustic pressure data is obtained for a range of observer polar angles mounted in the far field of the jets. Three nominal jet Mach numbers, namely 0.4, 0.6 and 0.8 are studied. Results suggest that the elliptic jets surveyed provide a noise reduction of the jet-surface installation noise source. The noise reduction is maximum in the forward arc and in the order of 1 dB for the fully-corrected overall sound pressure level data. Additionally, the noise benefit exists only when the minor axis of the elliptical nozzle is mounted parallel to the wing trailing edge. It is hypothesised that the reduction in the jet plume cross-section width limits the scattering of the near pressure field by the wing trailing edge to a lower frequency range. The jet mixing noise source, however, is seen to increase with decreasing nozzle exit-plane aspect ratio. The three jet velocities surveyed suggest the consistency of the key results discussed in the paper. Investigation of the jet turbulent flow structures and jet near pressure field is under way.

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Experimental Investigation into the Turbulence Flowfield of In-Flight Round Jets

Cited by 14 publications

References 23 publications

An experimental investigation into model-scale installed jet–pylon–wing noise

An experimental investigation into model-scale installed jet–pylon–wing noise

Aeroacoustic Analysis of a Subsonic Jet using the Discontinuous Galerkin Method

Far-field pressure measurements of elliptic jets discharged close to a wing

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