Acoustic Phenomena from Correctly Expanded Supersonic Jet Impinging on Inclined Plate

Akamine, Masahito; Nakanishi, Yuta; Okamoto, Koji; Teramoto, Shinji; Okunuki, Takeo; Tsutsumi, Seiji

doi:10.2514/1.j053953

Cited by 36 publications

(17 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The ideally expanded, 20-mm nozzle-diameter (D j ), Mach 1.8 jet is located at the Kashiwa Campus of the University of Tokyo. Although the facility is not anechoic, nearby reflecting surfaces were wrapped in fiberglass, resulting in good agreement 19 with anechoic far-field sound level measurements. 20 Calibrated acoustic pressure waveform data were synchronously acquired at five 2D intensity probes and a 40 D jradius arc with National Instruments PXI-4498 cards sampling at 204.8 kHz.…”

Section: Supersonic Jet Experimentsmentioning

confidence: 82%

Experimental validation of acoustic intensity bandwidth extension by phase unwrapping

Gee

Neilsen

Sommerfeldt

et al. 2017

The Journal of the Acoustical Society of America

Self Cite

View full text Add to dashboard Cite

The phase and amplitude gradient estimator (PAGE) method for active acoustic intensity uses pairwise microphone transfer functions to obtain the phase gradient, which improves the calculation bandwidth over the traditional weighted quadspectral method. Additionally, for broadband sources, the PAGE theory indicates that the transfer function phase can be unwrapped to further extend the usable frequency range to beyond the spatial Nyquist frequency. Here, two experiments demonstrate intensity bandwidth extension by more than an order of magnitude using phase unwrapping. First, plane-wave tube results show accurate one-dimensional intensity calculations with the microphones separated by five wavelengths, 30 times the traditional limit. Second, two-dimensional measurements of a laboratory-scale jet with a four-microphone probe yield physically reasonable calculations at frequencies 15 times the traditional limit.

show abstract

Section: Supersonic Jet Experimentsmentioning

confidence: 82%

Experimental validation of acoustic intensity bandwidth extension by phase unwrapping

Gee

Neilsen

Sommerfeldt

et al. 2017

The Journal of the Acoustical Society of America

Self Cite

View full text Add to dashboard Cite

show abstract

“…10 The 20 mm diameter ( ), converging-diverging nozzle was ideally expanded at Mach 1.8. Due to the non-anechoic environment, reflecting surfaces were wrapped in fiberglass as seen in Figure 2b.…”

Section: Methodsmentioning

confidence: 99%

Near-field spatial variation in similarity spectra decomposition of a Mach 1.8 laboratory-scale jet

Vaughn

Neilsen

Gee

et al. 2016

Proceedings of Meetings on Acoustics

Self Cite

View full text Add to dashboard Cite

“…This case has been studied extensively by Nakanishi et al, 34 Akamine et al, 35 and Tsutsumi et al, [36][37][38] and there is considerable experimental data (obtained at JAXA) available for comparison and solver validation purposes. The nozzle exit diameter, D = 20 mm, the Reynolds number based on D is Re =∼ 1.1 × 10 6 , 39 and the distance to the plate is L/D = 5 which causes the jet to impinge on the plate inside the potential core.…”

Section: Va Supersonic Jet Impinging On Inclined Platementioning

confidence: 98%

“…(16). This issue as well as Loci/CHEM validation against the free jet acoustic data available in the literature 39,43 are planned for detailed consideration during next stages of this study.…”

Section: Vb Supersonic Jet Impinging On Inclined Plate Including Inmentioning

confidence: 99%

Validation of Overset Discontinuous Galerkin and Hybrid RANS/LES Method for Jet Noise Prediction

Harris

Arslanbekov

Collins

et al. 2016

46th AIAA Fluid Dynamics Conference

View full text Add to dashboard Cite

Launch vehicles experience extreme acoustic loads during lift-off which are capable of damaging sensitive mechanical components of the vehicle and payload, and may lead to significant injury in passengers. The noise is driven by the exhaust plumes and their interaction with ground structures, and accurate prediction of this environment poses several unique challenges when compared to traditional jet noise modeling techniques. In particular, acoustic and Mach waves propagating from the exhaust plume are in the vicinity of obstructions and are generally in the nonlinear regime, which renders the classical acoustic analogy and linearized approaches invalid. This work continues the development of a recently introduced novel approach for the accurate prediction of lift-off acoustic environments. The method makes use of unstructured hybrid RANS/LES to predict the complex exhaust plume physics, and an overset high-order accurate discontinuous Galerkin solver to accurately propagate acoustic waves across large distances throughout the environment. The framework upon which the solvers are developed is described along with details outlining the overset grid assembly and interpolation methods. Detailed validation studies are presented to demonstrate the accuracy of the method for prediction of noise due to the impingement of a supersonic jet on a 45 degree inclined flat plate, and comparisons with experimental data show the method to be effective and accurate in terms of predicted overall sound pressure level spectra.

show abstract

Acoustic Phenomena from Correctly Expanded Supersonic Jet Impinging on Inclined Plate

Cited by 36 publications

References 16 publications

Experimental validation of acoustic intensity bandwidth extension by phase unwrapping

Experimental validation of acoustic intensity bandwidth extension by phase unwrapping

Near-field spatial variation in similarity spectra decomposition of a Mach 1.8 laboratory-scale jet

Validation of Overset Discontinuous Galerkin and Hybrid RANS/LES Method for Jet Noise Prediction

Contact Info

Product

Resources

About