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Статті в журналах з теми "Underexpanded flow"

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Автор: Grafiati

Опубліковано: 14 березня 2023

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1

Lee, K.-H., T. Setoguchi, S. Matsuo, and H.-D. Kim. "An experimental study of underexpanded sonic, coaxial, swirl jets." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 218, no. 1 (January 1, 2004): 93–103. http://dx.doi.org/10.1243/095440604322786974.

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Анотація:

The present study addresses experimental investigations of the near-field flow structures of an underexpanded sonic, dual, coaxial, swirl jet. The swirl stream is discharged from the secondary annular nozzle and the primary inner nozzle provides the underexpanded free jets. The interactions between the secondary swirl and primary underexpanded jets are quantified by a fine pitot impact and static pressure measurements and are visualized using a shadowgraph optical method. The pressure ratios of the secondary swirl and primary underexpanded jets are varied below 7.0. Experiments are conducted to investigate the effects of the secondary swirl stream on the primary underexpanded jets, compared with the secondary stream of no swirl. The results show that the presence of an annular swirl stream causes the Mach disc to move further downstream, with an increased diameter, and remarkably reduces the fluctuations of the impact pressures in the underexpanded sonic dual coaxial jet, compared with the case of the secondary annular stream with no swirl.

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2

Srinivasarao, T., P. Lovaraju, and E. Rathakrishnan. "Characteristics of Underexpanded Co-Flow Jets." Applied Mechanics and Materials 575 (June 2014): 507–11. http://dx.doi.org/10.4028/www.scientific.net/amm.575.507.

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The effect of inner nozzle lip thickness on the co-flow jet characteristics has been studied experimentally. Co-flow nozzles with inner nozzle lip thicknesses of 3 mm and 15 mm have been investigated. The thick-lip nozzle promotes mixing better than the thin-lip nozzle, for all the underexpanded operating conditions. The co-flow nozzle with thin-lip is effective in preserving the shock-cells nature, bringing down the longer shock-cell into shorter one and increasing the number of shock-cells compared to that of the co-flow nozzle with thick-lip.

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3

Cumber, P. S., M. Fairweather, S. A. E. G. Falle, and J. R. Giddings. "Predictions of the Structure of Turbulent, Highly Underexpanded Jets." Journal of Fluids Engineering 117, no. 4 (December 1, 1995): 599–604. http://dx.doi.org/10.1115/1.2817309.

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Анотація:

A mathematical model capable of predicting the shock and flow structure of turbulent, underexpanded jets is described. The model is based on solutions of the fluid flow equations obtained using a second-order accurate, finite-volume integration scheme together with an adaptive grid algorithm. Closure of these equations is achieved using a k-ε turbulence model coupled to the compressible dissipation rate correction proposed by Sarkar et al. (1991a). Extending earlier work which demonstrated the ability of this model to predict the structure of moderately underexpanded jets, the present paper compares model predictions and experimental data, reported in the literature, on a number of highly underexpanded releases. The results obtained demonstrate that the model yields reliable predictions of shock structure in the near field, inviscid region of such jets, while in the far field results derived using the compressibility corrected turbulence model are adequate for predicting mean flow properties, and are superior to those obtained using a standard k-ε approach.

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4

MATSUSHITA, Shinichi, Chungpyo HONG, Yutaka ASAKO, and Ichiro UENO. "G222 Underexpanded flow in a micro-tube." Proceedings of the Thermal Engineering Conference 2011 (2011): 355–56. http://dx.doi.org/10.1299/jsmeted.2011.355.

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5

Zaitsev, E. G. "Underexpanded wall jet in a cocurrent flow." Fluid Dynamics 28, no. 1 (1993): 149–52. http://dx.doi.org/10.1007/bf01055679.

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6

Yaga, Minoru, Yoshio Kinjo, Masumi Tamashiro, and Kenyu Oyakawa. "Flow characteristics of rectangular underexpanded impinging jets." Journal of Thermal Science 15, no. 1 (March 2006): 59–64. http://dx.doi.org/10.1007/s11630-006-0059-x.

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7

Sakakibara, Y., and J. Iwamoto. "Numerical Study of Oscillation Mechanism in Underexpanded Jet Impinging on Plate." Journal of Fluids Engineering 120, no. 3 (September 1, 1998): 477–81. http://dx.doi.org/10.1115/1.2820687.

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Анотація:

The mechanism of the oscillatory phenomena of an underexpanded jet impinging on a flat plate is studied numerically. Pressure changes generated in the flow field near the plate propagate radially in the surrounding region of the jet. The configuration of the jet boundary is changed by them and so, the waves forming the underexpanded jet are displaced when they are reflected from the jet boundary. And then, the pressure disturbances return to the region near the plate. Unsteady flow with repetition of growth and decay of the separation bubble on the plate is also found under certain conditions.

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8

Gubanov, Dmitriy, Valeriy Zapryagaev, and Nikolay Kiselev. "Flow Stucture of Supersonic Underexpanded Jet With Microjets Injection." Siberian Journal of Physics 8, no. 1 (March 1, 2013): 44–55. http://dx.doi.org/10.54362/1818-7919-2013-8-1-44-55.

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Experimental and numerical study of transversal microjets injection influence on the supersonic underexpanded jet flow structure has been performed. Data of measurements and calculation have acceptable agreement. Interaction of microjets with main supersonic jet sets to a decrease of an initial gasdynamic region. Microjets lead to a longitudinal streamwise vortices generation and a mushroom-like flow structures create on an external jet mixing layer. Dissipation of longitudinal streamwise vortices was observed at the second jet cell. Complex gasdynamic flow structure of the supersonic underexpanded jet interacting with supersonic microjets has been studied for the first time. This structure contains system of complex chock waves and expansion waves spreading from the position of the impact microjets/main jet localization place. Future of interaction process a chock-wave structure of main jet with additional shock waves has been studied

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9

Sakakibara, Yoko, Masaki Endo, and Junjiro Iwamoto. "On Flow Field of Radially Emitted Underexpanded Jet." International Journal of Aeroacoustics 12, no. 5-6 (October 2013): 423–35. http://dx.doi.org/10.1260/1475-472x.12.5-6.423.

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10

Arun Kumar, R., and G. Rajesh. "Shock transformation and hysteresis in underexpanded confined jets." Journal of Fluid Mechanics 823 (June 21, 2017): 538–61. http://dx.doi.org/10.1017/jfm.2017.231.

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Анотація:

This study investigates the shock transformation in an underexpanded jet in a confined duct when the jet total pressure is increased. Experimental study reveals that the Mach reflection (MR) in the fully underexpanded jet transforms to a regular reflection (RR) at a certain jet total pressure. It is observed that neither the incident shock angle nor the upstream Mach number varies during the MR–RR shock transformation. This is in contradiction to the classical MR–RR transformations in internal flow over wedges and in underexpanded open jets. This transformation is found to be a total pressure variation induced transformation, which is a new kind of shock transformation. The present study also reveals that the critical jet total pressures for MR–RR and RR–MR transformations are not the same when the primary pressure is increasing and decreasing, suggesting a hysteresis in the shock transformations.

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11

Xu, Q., D. Cheng, G. Trapaga, N. Yang, and E. J. Lavernia. "Numerical Analyses of Fluid Dynamics of an Atomization Configuration." Journal of Materials Research 17, no. 1 (January 2002): 156–66. http://dx.doi.org/10.1557/jmr.2002.0024.

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Computational fluid dynamic techniques were used to analyze the gas flow behavior of a typical atomization configuration. The calculated results are summarized as follows. The atomization gas flow at the atomizer's exit may be either subsonic at ambient pressure or sonic at an underexpanded condition, depending on the magnitude of the inlet gas pressure. When the atomization gas separates to become a free annular gas jet, a closed recirculating vortex region is formed between the liquid delivery tube and the annular jet's inner boundary. Upon entering the atomization chamber, an underexpanded sonic gas flow is further accelerated to supersonic velocity during expansion. This pressure adjustment establishes itself in repetitive expansion and compression waves. A certain protrusion of the liquid delivery tube is crucial to obtain a stable subatmospheric pressure region at its exit. The vortex flow under the liquid delivery tube tends to transport liquid metal to the high kinetic energy gas located outside the liquid delivery tube, thereby leading to an efficient atomization.

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12

Moustafa, G. H. "Further study of high speed single free jets." Aeronautical Journal 97, no. 965 (May 1993): 171–76. http://dx.doi.org/10.1017/s0001924000026129.

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AbstractExperiments to study the behaviour of a compressible free jet issuing from an axisymmetric convergent nozzle are reported. Detailed measurements of the mean flow field for subsonic, sonic and underexpanded sonic jets was made within the pressure ratio range of 1.13 to 4. The results show that the spread and decay rates of the jet vary significantly with pressure ratio. The results further indicate the radial velocity/total pressure collapse within the two-dimensional shear layer data. The underexpanded jet propagates to a greater distance downstream than the low speed jets; this leads to enhancement of the far field mixing.

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13

Cumber, P. S., M. Fairweather, S. A. E. G. Falle, and J. R. Giddings. "Predictions of the Structure of Turbulent, Moderately Underexpanded Jets." Journal of Fluids Engineering 116, no. 4 (December 1, 1994): 707–13. http://dx.doi.org/10.1115/1.2911839.

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Анотація:

A mathematical model capable of predicting the structure of turbulent, underexpanded jets is described. The model is based on solutions of the fluid flow equations obtained using a second-order accurate, finite-volume integration scheme coupled to an adaptive grid algorithm. Turbulence within these jets is modelled using a k-ε approach coupled to the compressible dissipation rate model of Sarkar et al. (1991a). Comparison of model predictions and experimental data, reported in the literature, on a number of moderately underexpanded jets demonstrate significant improvements over results derived using the standard k-ε approach, and the adequacy of the compressibility corrected turbulence model for predicting such jets.

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14

Verma, S. B., and E. Rathakrishnan. "Flow and Acoustic Properties of Underexpanded Elliptic-Slot Jets." Journal of Propulsion and Power 17, no. 1 (January 2001): 49–57. http://dx.doi.org/10.2514/2.5706.

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15

KASHIMURA, Hideo, and Tsuyoshi YASUNOBU. "Self Oscillation of Underexpanded Impinging Jet with Annular flow." Journal of the Visualization Society of Japan 14, Supplement2 (1994): 23–26. http://dx.doi.org/10.3154/jvs.14.supplement2_23.

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16

Morita, Nobuyoshi, and Toshio Yokomizo. "709 Underexpanded sonic flow from nozzle confined curved wall." Proceedings of Yamanashi District Conference 2000 (2000): 219–20. http://dx.doi.org/10.1299/jsmeyamanashi.2000.219.

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17

SAKAKIBARA, Yoko, Masaki ENDO, and Junjiro IWAMOTO. "A Study on Flow Field of Radial Underexpanded Jet." Transactions of the Japan Society of Mechanical Engineers Series B 71, no. 712 (2005): 2922–27. http://dx.doi.org/10.1299/kikaib.71.2922.

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18

NAKAMURA, Tomoyuki, and Junjiro IWAMOTO. "Experimental Study on Flow Structure and Oscillation of Underexpanded Impinging Jet Flow." Journal of the Visualization Society of Japan 16, Supplement2 (1996): 211–14. http://dx.doi.org/10.3154/jvs.16.supplement2_211.

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19

Satyajit, De, and Ethirajan Rathakrishnan. "Experimental study of supersonic co-flowing jet." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 4 (January 9, 2018): 1237–49. http://dx.doi.org/10.1177/0954410017749866.

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A detailed experimental study was carried out to investigate the behaviour of a Mach 2 primary jet in the presence of a Mach 1.6 annular co-flow. The lip thickness of the inner nozzle was 7.75 mm. The characteristics of jets were investigated at nozzle pressure ratios 3 to 8, in steps of 1. At nozzle pressure ratios 3 to 7, the centre jet is overexpanded; and at nozzle pressure ratio 8, it is marginally underexpanded. Both primary and secondary jets were operated at the nozzle pressure ratio. Centreline pressure distribution was measured to examine the supersonic core length of the centre jet in the presence and absence of the co-flow at all nozzle pressure ratios. It is found that the co-flow reduces the core length of the primary jet at all overexpanded states. A maximum core length reduction of about 61% is at nozzle pressure ratio 4, whereas the core increases by 5% at the marginally underexpanded state corresponding to nozzle pressure ratio 8. The co-flow jet merges with the primary jet at 4 D, at nozzle pressure ratio 3, and at 8 D for nozzle pressure ratios above 4. Shadowgraph images of the jet in the presence and absence of co-flow reveal that the waves in the core of the jet are strongly influenced by the co-flow.

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20

Thawko, A., R. van Hout, H. Yadav, and L. Tartakovsky. "Flow field characteristics of a confined, underexpanded transient round jet." Physics of Fluids 33, no. 8 (August 2021): 085104. http://dx.doi.org/10.1063/5.0056343.

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21

SAKAKIBARA, Yoko, Masaki ENDO, and Junjiro IWAMOTO. "21301 A Study on Flow Field around Radial Underexpanded Jet." Proceedings of Conference of Kanto Branch 2005.11 (2005): 443–44. http://dx.doi.org/10.1299/jsmekanto.2005.11.443.

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22

WACHI, Daisuke, and Junjiro IWAMOTO. "711 Flow field and noise generation of underexpanded impinging jet." Proceedings of Conference of Hokuriku-Shinetsu Branch 2000.37 (2000): 269–70. http://dx.doi.org/10.1299/jsmehs.2000.37.269.

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23

Banholzer, M., W. Vera-Tudela, C. Traxinger, M. Pfitzner, Y. Wright, and K. Boulouchos. "Numerical investigation of the flow characteristics of underexpanded methane jets." Physics of Fluids 31, no. 5 (May 2019): 056105. http://dx.doi.org/10.1063/1.5092776.

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24

Gorshkov, G. F., V. N. Uskov, and V. S. Favorskii. "Nonstationary flow of an underexpanded jet around an unbounded obstacle." Journal of Applied Mechanics and Technical Physics 34, no. 4 (1994): 503–8. http://dx.doi.org/10.1007/bf00851465.

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25

Zapryagaev, V. I., and A. V. Solotchin. "Three-dimensional structure of flow in a supersonic underexpanded jet." Journal of Applied Mechanics and Technical Physics 32, no. 4 (1992): 503–7. http://dx.doi.org/10.1007/bf00851550.

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26

Li, Xiaopeng, Rui Zhou, Wei Yao, and Xuejun Fan. "Flow characteristic of highly underexpanded jets from various nozzle geometries." Applied Thermal Engineering 125 (October 2017): 240–53. http://dx.doi.org/10.1016/j.applthermaleng.2017.07.002.

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27

Zheng, Xie, Xie Jian, Jiang Wei, and Du Wenzheng. "Numerical and Experimental Investigation of Near-Field Mixing in Parallel Dual Round Jets." International Journal of Aerospace Engineering 2016 (2016): 1–12. http://dx.doi.org/10.1155/2016/7935101.

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Анотація:

Parallel underexpanded round jets system has been widely used in engineering applications, and the flow field structures are very complex because of the jets interaction. In this paper, we studied the near-field mixing phenomenon in parallel dual underexpanded jets numerically by solving the Reynolds-Averaged Navier-Stokes Equations. The numerical results agree well with experimental data acquired by particle image velocimetry. Similar to plane jets, to some degree, two round jets are deflected towards the dual nozzle symmetry plane; the flow field can also be divided into three regions. Meanwhile, attempts have been made to predict merge point and combine point locations on certain cross profile of computational domain by correlating them with jet spacing and jet pressure ratio. The jet spacing plays an important role in jets interaction, and jet interaction decreases with the increase in jet spacing. The jets interaction in terms of merge (combine) point and pressure varies significantly while the jet spacing differs. Additionally, as pressure ratio increases, the effect of jet interaction decreases, and the merge (combine) point location moves downstream.

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28

Verma, S. B., and E. Rathakrishnan. "Noisefield of Underexpanded Notched Circular-Slot Jets." Noise & Vibration Worldwide 33, no. 6 (June 2002): 9–23. http://dx.doi.org/10.1260/095745602320777222.

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The effect of notches on the flow and noise field of jets from circular-slots is experimentally investigated. Three types of slot geometries, namely, semicircular, triangular and square are studied. The results demonstrate that the presence of the notch introduces a slight aspect-ratio in the initial circular-slot geometry so that the notched jet exhibits characteristics, similar to jets exiting from non-circular geometries. At underexpanded condition, additional expansion and compression waves are observed to emanate from the region of notches that modifies the jet development and results in a reduction in the average shock-cell length, which is accompanied by a reduction in far-field shock associated noise. The acoustic spectrum of the radiated shock noise indicates that notch geometry variation strongly alters the acoustic emission characteristics of these jets both in the screech component and broadband shock associated noise.

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29

Hansen, E. C. "Experimental and Analytical Study of Flow Diversion Beyond an Underexpanded Nozzle." Journal of Fluids Engineering 113, no. 3 (September 1, 1991): 475–78. http://dx.doi.org/10.1115/1.2909520.

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A steady-state flow apparatus was used to investigate the process of gun gas diversion through a single hole perforated disk diverter. The amount of diverted flow was found to depend on the distance between the nozzle and the diverter disk and the ratio of nozzle pressure to diverter exit pressure. Experimental studies used nitrogen and carbon dioxide as the working fluids to show the effect of specific heat ratio. At ratios of nozzle pressure to ambient pressure ranging from 4 to 60 diversion efficiencies of 50 to 99 percent were produced. A one-dimensional analytic gas flow model was developed. Results of the analytic model paralleled the experimental data for pressure ratios over 10.

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30

Cui, Wei, Jinglei Xu, Bing-Chen Wang, Pu Zhang, and Qihao Qin. "The initial flow structures and oscillations of an underexpanded impinging jet." Aerospace Science and Technology 115 (August 2021): 106740. http://dx.doi.org/10.1016/j.ast.2021.106740.

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31

Gojon, Romain, and Christophe Bogey. "Flow Structure Oscillations and Tone Production in Underexpanded Impinging Round Jets." AIAA Journal 55, no. 6 (June 2017): 1792–805. http://dx.doi.org/10.2514/1.j055618.

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32

KASHIMURA, Hideo, and Tsuyoshi YASUNOBU. "Visualization of Self Induced Flow Oscillation in an Underexpanded Sonic Jet." Journal of the Visualization Society of Japan 11, Supplement2 (1991): 31–34. http://dx.doi.org/10.3154/jvs.11.supplement2_31.

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33

SERYU, Ryota, and Junjiro IWAMOTO. "20906 Quantification for Flow Field of Underexpanded Jet Impinging on Cone." Proceedings of Conference of Kanto Branch 2009.15 (2009): 389–90. http://dx.doi.org/10.1299/jsmekanto.2009.15.389.

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34

Dam, N. J., M. Rodenburg, R. A. L. Tolboom, G. G. M. Stoffels, P. M. Huisman-Kleinherenbrink, and J. J. ter Meulen. "Imaging of an underexpanded nozzle flow by UV laser Rayleigh scattering." Experiments in Fluids 24, no. 2 (February 20, 1998): 93–101. http://dx.doi.org/10.1007/s003480050156.

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35

Hu, Tieh-Feng, and D. K. McLaughlin. "Flow and acoustic properties of low Reynolds number underexpanded supersonic jets." Journal of Sound and Vibration 141, no. 3 (September 1990): 485–505. http://dx.doi.org/10.1016/0022-460x(90)90640-l.

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36

PANDA, J. "Shock oscillation in underexpanded screeching jets." Journal of Fluid Mechanics 363 (May 25, 1998): 173–98. http://dx.doi.org/10.1017/s0022112098008842.

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Анотація:

The periodic oscillation of the shock waves in screeching, underexpanded, supersonic jets, issuing from a choked, axisymmetric, nozzle at fully expanded Mach numbers (Mj) of 1.19 and 1.42, is studied experimentally and analytically. The experimental part uses schlieren photography and a new shock detection technique which depends on a recently observed phenomenon of laser light scattering by shock waves. A narrow laser beam is traversed from point to point in the flow field and the appearance of the scattered light is sensed by a photomultiplier tube (PMT). The time-averaged and phase-averaged statistics of the PMT data provide significant insight into the shock motion. It is found that the shocks move the most in the jet core and the least in the shear layer. This is opposite to the intuitive expectation of a larger-amplitude shock motion in the shear layer where organized vortices interact with the shock. The mode of shock motion is the same as that of the emitted screech tone. The instantaneous profiles of the first four shocks over an oscillation cycle were constructed through a detailed phase averaged measurement. Such data show a splitting of each shock (except for the first one) into two weaker ones through a ‘moving staircase-like’ motion. During a cycle of motion the downstream shock progressively fades away while a new shock appears upstream. Spark schlieren photographs demonstrate that a periodic convection of large organized vortices over the shock train results in the above described behaviour. An analytical formulation is constructed to determine the self-excitation of the jet column by the screech sound. The screech waves, while propagating over the jet column, add a periodic pressure fluctuation to the ambient level, which in turn perturbs the pressure distribution inside the jet. The oscillation amplitude of the first shock predicted from this linear analysis shows reasonable agreement with the measured data. Additional reasons for shock oscillation, such as a periodic perturbation of the shock formation mechanism owing to the passage of the organized structures, are also discussed.

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37

Kiryushina, Maria Alexandrovna, and Tatiana Gennadyevna Elizarova. "Modelling of nozzle start-up for underexpanded jet generation." Keldysh Institute Preprints, no. 59 (2021): 1–30. http://dx.doi.org/10.20948/prepr-2021-59.

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A numerical simulation of hydrogen jet in the micronozzle is carried out, which is used as the main element in the experimental installation to study the properties of rarefied gases at high speeds and low temperatures. The features of the transient jet flow - pressure gradients, velocities and the complex geometry of the problem are uniformly described within the framework of the quasi-gas dynamic algorithm included in the open platform OpenFOAM.

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38

Zapryagaev, Valeriy, Ivan Kavun, and Nikolay Kiselev. "Flow Feature in Supersonic Non-Isobaric Jet near the Nozzle Edge." Aerospace 9, no. 7 (July 13, 2022): 379. http://dx.doi.org/10.3390/aerospace9070379.

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Using the example of studying the supersonic underexpanded jet initial section, the issue of interpreting the experimental visualization data and Pitot pressure measurement data using the results of numerical calculations (2d RANS k-ω SST) is discussed. It is shown that the gradient S-shaped feature of the gas-dynamic structure near the nozzle exit, observed in the form of a barrel shock, is a characteristic that separates the expansion and compression regions, and downstream is transformed into a barrel shock. It has been established that the reason for the observed S-shaped curvature of this feature is the axisymmetric nature of the jet flow.

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39

Pashchina, A. S. "Measurements of electron number density and temperature in a supersonic plasma jet by optical emission spectroscopy." Journal of Physics: Conference Series 2100, no. 1 (November 1, 2021): 012003. http://dx.doi.org/10.1088/1742-6596/2100/1/012003.

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Abstract The results of experimental studies of the shock-wave region of the supersonic plasma jet flow formed by a pulsed capillary discharge with a polymeric wall are presented. Using optical emission spectroscopy of high spatial resolution, a detailed picture of the evolution of the radial profiles of the electron number density and temperature along the initial section of an underexpanded plasma jet, starting from the capillary outlet and ending with the flow stagnation zone, has been obtained. It was found that the profiles of the electron number density and temperature reflect all the features of the shock-wave flow region, tracing the influence of intercepting, central and reflected shock waves.

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40

Fillingham, Patrick, and Igor V. Novosselov. "Wall jet similarity of impinging planar underexpanded jets." International Journal of Heat and Fluid Flow 81 (February 2020): 108516. http://dx.doi.org/10.1016/j.ijheatfluidflow.2019.108516.

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41

Ishii, R., Y. Umeda, and M. Yuhi. "Numerical analysis of gas-particle two-phase flows." Journal of Fluid Mechanics 203 (June 1989): 475–515. http://dx.doi.org/10.1017/s0022112089001552.

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This paper is concerned with a numerical analysis of axisymmetric gas-particle two-phase flows. Underexpanded supersonic free-jet flows and supersonic flows around a truncated cylinder of gas-particle mixtures are solved numerically on the super computer Fujitsu VP-400. The gas phase is treated as a continuum medium, and the particle phase is treated partly as a discrete one. The particle cloud is divided into a large number of small clouds. In each cloud, the particles are approximated to have the same velocity and temperature. The particle flow field is obtained by following these individual clouds separately in the whole computational domain. In estimating the momentum and heat transfer rates from the particle phase to the gas phase, the contributions from these clouds are averaged over some volume whose characteristic length is small compared with the characteristic length of the flow field but large compared with that of the clouds. The results so obtained reveal that the flow characteristics of the gas-particle mixtures are widely different from those of the dust-free gas at many points.

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42

Wang, Ye, Kun Wu, Wei Yao, and Xuejun Fan. "Flow Modulation and Mixing Enhancement of Highly Underexpanded Jet by Vortex Excitation." AIAA Journal 58, no. 6 (June 2020): 2462–74. http://dx.doi.org/10.2514/1.j058476.

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43

Gojon, Romain, and Christophe Bogey. "Flow Features near Plate Impinged by Ideally Expanded and Underexpanded Round Jets." AIAA Journal 56, no. 2 (February 2018): 445–57. http://dx.doi.org/10.2514/1.j056421.

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44

Gordeev, A. N., A. F. Kolesnikov, and V. I. Sakharov. "Flow and heat transfer in underexpanded nonequilibrium jets of an induction plasmatron." Fluid Dynamics 46, no. 4 (August 2011): 623–33. http://dx.doi.org/10.1134/s0015462811040120.

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45

Mironov, S. G., V. M. Aniskin, and A. A. Maslov. "The effect of underexpanded jet flow conditions on the supersonic core length." Journal of Physics: Conference Series 1359 (November 2019): 012014. http://dx.doi.org/10.1088/1742-6596/1359/1/012014.

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46

Menon, Nandkishore, and Beric William Skews. "Shock wave configurations and flow structures in non-axisymmetric underexpanded sonic jets." Shock Waves 20, no. 3 (May 21, 2010): 175–90. http://dx.doi.org/10.1007/s00193-010-0257-z.

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47

MATSUOKA, Takeshi, Tsuyoshi YASUNOBU, and Hideo KASHIMURA. "Characteristics of Flow Field Caused by Underexpanded Supersonic Jet Impinging Flat Plate." Proceedings of Conference of Chugoku-Shikoku Branch 2002 (2002): 217–18. http://dx.doi.org/10.1299/jsmecs.2002.217.

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48

Liu, Shi Nian, Wei Su, and Zeng Fu Wei. "Flow Field Simulation of the Nozzle and the Influence of Size." Applied Mechanics and Materials 437 (October 2013): 47–50. http://dx.doi.org/10.4028/www.scientific.net/amm.437.47.

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The nozzle is one of the critical parts in the dry-ice blasting system, spray nozzle's structure and the air supersonic free jet flow field take big influence on cleaning efficiency during the blasting process. Inner flow field of different size nozzles and the flow field of jet flow sprayed by nozzles were simulated with software Fluent, which obtained the distribution results of pressure and velocity of fluid. The result indicated that the supersonic underexpanded jet take place in the nozzle outlet and the shock wave is gained as the pressure at the nozzle exit is greater than the atmospheric pressure. With increasing of the nozzle size, the velocity decrease of airflow become slower, the shock wave transmission distance increase and deduce the stability of the jet flow.

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49

Волков, К. Н., В. Н. Емельянов, А. В. Ефремов та А. И. Цветков. "Структура течения и колебания давления при взаимодействии сверхзвуковой недорасширенной струи газа с трубной полостью". Журнал технической физики 90, № 8 (2020): 1254. http://dx.doi.org/10.21883/jtf.2020.08.49534.328-19.

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Supersonic jets are widely used in devices based on the phenomenon of a self-oscillating process that occurs when a gas flow interacts with circular cavities (gas-jet sound emitters). The mechanisms of maintaining undamped pressure oscillations and determining the flow field in the tube cavity during the interaction of a supersonic underexpanded jet with cavity are considered. The physical pattern of the flow in the cavity of a gas-jet emitter is discussed, the existence of odd longitudinal modes is shown, and wave diagrams are proposed for describing the flow in odd longitudinal modes. The wave diagrams are based on the analysis of the signals of piezoelectric sensors, recording pressure oscillations in the tube cavity. The calculation of the flow parameters in the tube cavity in longitudinal modes is based on the flow velocity and speed of sound diagram.

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50

Samanta, Arnab, S. Narayanan, Shailesh Kumar Jha, and Ashish Narayan. "Numerical simulation of a sonic-underexpanded jet impinging on a partially covered cylindrical Hartmann whistle." SIMULATION 94, no. 8 (November 17, 2017): 707–21. http://dx.doi.org/10.1177/0037549717741202.

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The present study numerically investigates the effect of a partially covered cylindrical shield on the flow/shock oscillation characteristics of a Hartmann whistle when the pulsating jet exits through the two small openings, (a) close to the cavity inlet, and (b) away from the cavity inlet, of the cylindrical shield. The relevant parameters that modify the flow/shock oscillations of the Hartmann whistle are the stand-off distance, nozzle pressure ratio, cavity length, cavity shield, jet diameter, etc. The pulsating nature of flow in a partially shielded Hartmann whistle is investigated for various stand-off distances to understand its effect in achieving effective flow control. The velocity vectors indicate that the partly shielded Hartmann whistle operates in the jet regurgitant mode with different regurgitant phases. It also shows that some amount of the jet near the cavity inlet gets diverted towards the shield and gets attached to it, whereas some exits out through the two shield openings which can be injected into the flow to be controlled. The Mach number contours indicate the flow deceleration/reacceleration zones, shock-cell structures as well as fluid column oscillations in shock-cells/cavity regions. The present study reveals that the stand-off distance and the jet diameter are the crucial parameters, which control the oscillation mechanisms in a partially covered Hartmann whistle for achieving effective flow control. Thus, this paper sufficiently demonstrates the role of stand-off distances, openings in the shield as well as jet diameter in modifying the flow/shock oscillation characteristics of a partially shielded Hartmann whistle in achieving the finest flow control.

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