Experimental and Numerical Investigation of Flow Properties of Supersonic Helium-Air Jets

Miller, Steven A.; Veltin, Jérémy

doi:10.2514/1.j050720

Cited by 34 publications

(4 citation statements)

References 16 publications

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“…Doty and McLaughlin [24] and Papamoschou [25] have shown that mixtures of helium and air can appropriately simulate the noise of heated jets to a reasonable accuracy. Miller and Veltin [26] showed a good agreement of the mean flow properties between experimental data from helium-air mixture jets and a numerical calculation of heated air jets. Recent careful comparisons [27] between the measurements conducted at Pennsylvania State University with the measurements performed in other facilities have shown very good agreement when matching the acoustic velocity of the helium-air mixture jet to that of a heated jet following a procedure developed by Doty and McLaughlin [24] over 10 years ago.…”

Section: A Facility and Instrumentation Descriptionsmentioning

confidence: 68%

Effects of Jet Temperature on Broadband Shock-Associated Noise

et al. 2015

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This paper describes an experimental study of the effects of jet heating on broadband shock-associated noise. The noise measurements are supplemented with schlieren flow visualizations that show that the appearance of a Mach disk in the shock cell structure is consistent with the saturation of the broadband shock-associated noise levels for both highly under-and overexpanded jets. The effects of jet heating are then described for the design Mach-number-1.5 nozzle operating at four Mach numbers: two overexpanded (M j 1.2 and 1.4), and two underexpanded (M j 1.7 and 1.9). Total temperature ratios in the range of 1.0 to 2.2 are considered in increments of 0.2. These values are chosen to supplement heated air measurements at higher total temperature ratios (between 1.8 to 3.2) and to examine the effects of low levels of heating. It is shown that the peak broadband shock-associated noise rapidly approaches a saturation value in all cases. In the underexpanded cases, the peak broadband shock-associated noise level decreases with increasing total temperature ratio and the reverse is true for the overexpanded cases. Although the changes are very small, a systematic trend can be observed. The spectral shape of fundamental broadband shock-associated noise is found to be very similar for all the cases considered. An empirical prediction model for the fundamental broadband shock-associated noise is proposed. Nomenclature a ∞ = ambient acoustic velocity D = exit diameter of the nozzle D j = fully expanded diameter of the jet plume f = frequency f c = characteristic frequency; U j ∕D j I = intensity of shock noise L = shock cell spacing M a = acoustic Mach number; U j ∕a ∞ M c = convective Mach number; U c ∕a ∞ M d = design Mach number of the nozzle M j = average Mach number of the fully expanded jet R = physical distance of the microphones from the jet exit R e = Reynolds number R prop = propagation distance for the acoustic measurements T o = jet stagnation temperature T ∞ = ambient temperature St = Strouhal number; f∕f c U c

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Section: A Facility and Instrumentation Descriptionsmentioning

confidence: 68%

Effects of Jet Temperature on Broadband Shock-Associated Noise

et al. 2015

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“…20 Kinzie and McLaughlin 21 and Papamoschou 22 have shown that mixtures of helium and air can appropriately replicate the aeroacoustics of heated jets to a reasonable accuracy by matching the acoustic velocity of the heated gas. Miller and Veltin 23 showed a good agreement of the flow properties between the experimental data from helium-air mixture jets and the numerical RANS calculations of heated air jets. Additionally, a comparison between experimental data from the laboratory helium-air jets in the High Speed Jet Aeroacoustics Facility at Penn State and the moderate-scale heated jet noise facility at NASA GRC was made.…”

Section: Technical Approach Facility Description and Overviewmentioning

confidence: 64%

Acoustics measurements of military-style supersonic beveled nozzle jets with interior corrugations

Powers

McLaughlin

2016

International Journal of Aeroacoustics

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Increasingly powerful and noisy military aircraft have generated the need for research leading to the development of supersonic jet noise reduction devices. The hot, high speed supersonic jets exhausting from military aircraft during takeoff present a most challenging problem. The present study extends prior research on two methods of noise reduction. The first is the internal nozzle corrugations pioneered by Seiner et al. and the second is the beveled exit plane explored most recently by Viswanathan. A novel research idea of creating fluidic corrugations similar to the nozzle corrugations has been initiated by Penn State. To further the understanding and analysis of the fluidic corrugations, the present study focuses on the flow field and acoustic field of nozzles with two, three, and six conventional, hardwalled corrugations. The effect of the combination of the internal corrugations with a beveled nozzle is explored. The results show that significant noise reductions of over 3 dB of the mixing noise and the broadband shock-associated noise can be achieved. The combination of the beveled nozzle and the internal nozzle corrugations showed that there is less azimuthal dependence of the acoustic field than for the purely beveled nozzle. The combination nozzle was shown to reduce the noise over a wider range of polar angles and operating conditions than either the purely beveled nozzle or the purely corrugated nozzle.

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“…The mixture’s total pressure is controlled to within 5% of the target value during data acquisition. This methodology, developed by Kinzie 35 and Doty and McLaughlin, 36 has been demonstrated to accurately replicate the noise 37 and velocity profiles 38 of heated air jets. A comparison between experimental data from model-scale heat-simulated jets in the high-speed jet aeroacoustics facility at Penn State and the moderate-scale heated jet noise facility at NASA Glenn Research Center, which show excellent agreement, can be found in McLaughlin et al 39…”

Section: Experimental Approachmentioning

confidence: 99%

Leveraging large eddy simulations to assess noise source imaging of a controlled supersonic jet

Prasad

Hromisin

Morris

2022

International Journal of Aeroacoustics

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Noise source imaging based on phased array measurements is an essential tool in the aeroacoustic analysis of new nozzle designs, especially at full-scale. This investigation aims to assess the capability of a deconvolution-based beamforming technique to accurately estimate the changes in noise sources for model-scale heated military jets when fluid inserts are used for noise control. This goal is achieved by performing well-validated Large Eddy Simulations (LES) to complement the experimental measurements. The LES data is segregated into its hydrodynamic, acoustic and thermal components using Doak’s Momentum Potential Theory (MPT). The near-field MPT-derived components are subjected to Spectral Proper Orthogonal Decomposition (SPOD) to compare with the frequency-dependent noise source maps obtained directly from experiments. It is shown that fluid inserts alter the naturally occurring Kelvin-Helmholtz (K-H) instability in the jet shear layer, which leads to a change in the directivity of the noise radiated in the near-field. The upstream shift in the noise source distribution resulting from the modified K-H instability is accurately captured by the deconvolution-based source imaging technique using just the far-field measurements. These changes in source locations as a function of frequency are documented.

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Experimental and Numerical Investigation of Flow Properties of Supersonic Helium-Air Jets

Cited by 34 publications

References 16 publications

Effects of Jet Temperature on Broadband Shock-Associated Noise

Effects of Jet Temperature on Broadband Shock-Associated Noise

Acoustics measurements of military-style supersonic beveled nozzle jets with interior corrugations

Leveraging large eddy simulations to assess noise source imaging of a controlled supersonic jet

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