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Journal articles on the topic 'Subsonic'

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Published: 4 June 2021
Last updated: 12 February 2022

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1

Heins, Paul, and S. Perkins. "Subsonic Booms." Science News 164, no. 18 (November 1, 2003): 287. http://dx.doi.org/10.2307/4018958.

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2

Zhu, Wen-Xiang, and Wei Liu. "Magnetic snakes subsonic." AME Medical Journal 5 (December 2020): 44. http://dx.doi.org/10.21037/amj.2020.03.01.

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3

Salo, Janne, and Martti M. Salomaa. "Subsonic nondiffracting waves." Acoustics Research Letters Online 2, no. 1 (January 2001): 31–36. http://dx.doi.org/10.1121/1.1350398.

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4

Loseva, T. V., and I. V. Nemchinov. "Subsonic radiation waves." Fluid Dynamics 28, no. 5 (1994): 720–33. http://dx.doi.org/10.1007/bf01050059.

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5

Xie, Chunjing, and Zhouping Xin. "Global subsonic and subsonic-sonic flows through infinitely long nozzles." Indiana University Mathematics Journal 56, no. 6 (2007): 2991–3024. http://dx.doi.org/10.1512/iumj.2007.56.3108.

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6

Florin, MUNTEANU, OPREAN Corneliu, and STOICA Corneliu. "INCAS SUBSONIC WIND TUNNEL." INCAS BULLETIN 1, no. 1 (September 24, 2009): 12–14. http://dx.doi.org/10.13111/2066-8201.2009.1.1.3.

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7

Somers, D. M. "Subsonic aerofoil design 2010." Aeronautical Journal 115, no. 1165 (March 2011): 137–46. http://dx.doi.org/10.1017/s0001924000005546.

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Abstract The state of the art as practiced by a handful of aerofoil designers is discussed. The methods used, both theoretical and experimental, are described. Aerofoil/application design integration and expansion of the design envelope to lower and higher Reynolds numbers are illustrated by examples, including the slotted, natural-laminar-flow aerofoil.
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8

Moosavi, M. R., A. R. Naddaf Oskouei, and A. Khelil. "Flutter of subsonic wing." Thin-Walled Structures 43, no. 4 (April 2005): 617–27. http://dx.doi.org/10.1016/j.tws.2004.10.001.

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9

Cheng, Jianfeng, and Lili Du. "Compressible Subsonic Impinging Flows." Archive for Rational Mechanics and Analysis 230, no. 2 (May 15, 2018): 427–58. http://dx.doi.org/10.1007/s00205-018-1249-x.

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10

Xie, Chunjing, and Zhouping Xin. "Global subsonic and subsonic-sonic flows through infinitely long axially symmetric nozzles." Journal of Differential Equations 248, no. 11 (June 2010): 2657–83. http://dx.doi.org/10.1016/j.jde.2010.02.007.

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11

Barnett, D. M. "Boundary-polarized subsonic Rayleigh waves under conditions of semi-simple Stroh degeneracy." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 475, no. 2231 (November 2019): 20190658. http://dx.doi.org/10.1098/rspa.2019.0658.

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We undertake a study of subsonic free surface (Rayleigh) waves in linear elastic half-spaces of general anisotropy when the wave polarization vector lies in the half-space boundary , if and when the formalism due to A. N. Stroh exhibits semi-simple degeneracy at the Rayleigh speed v R . It is shown that the class of subsonic steady wave motions at any subsonic velocity exhibiting semi-simple degeneracy includes a free surface wave whenever the first transonic state is not exceptional, in accordance with general surface wave theory. Furthermore, such a free surface wave is always necessarily boundary-polarized ! In general, the restrictions on the half-space elastic constants permitting the existence of semi-simplicity in steady motion at a subsonic phase speed are not satisfied in any physically realized medium which is elastically stable, but we outline an algorithm which allows one to construct the elastic stiffnesses of media which exist mathematically and allow for the existence of subsonic free surface waves (which are necessarily boundary-polarized) under conditions of semi-simple degeneracy in the sense of Stroh's formalism.
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12

V. Kozlov, Victor, Genrich R. Grek, Alexander V. Dovgal, and Yury A. Litvinenko. "Stability of Subsonic Jet Flows." Journal of Flow Control, Measurement & Visualization 01, no. 03 (2013): 94–101. http://dx.doi.org/10.4236/jfcmv.2013.13012.

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13

Cavalieri, André V. G., Peter Jordan, Tim Colonius, and Yves Gervais. "Axisymmetric superdirectivity in subsonic jets." Journal of Fluid Mechanics 704 (July 3, 2012): 388–420. http://dx.doi.org/10.1017/jfm.2012.247.

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AbstractWe present experimental results for the acoustic field of jets with Mach numbers between 0.35 and 0.6. An azimuthal ring array of six microphones, whose polar angle, $\theta $, was progressively varied, allows the decomposition of the acoustic pressure into azimuthal Fourier modes. In agreement with past observations, the sound field for low polar angles (measured with respect to the jet axis) is found to be dominated by the axisymmetric mode, particularly at the peak Strouhal number. The axisymmetric mode of the acoustic field can be clearly associated with an axially non-compact source, in the form of a wavepacket: the sound pressure level for peak frequencies is found be superdirective for all Mach numbers considered, with exponential decay as a function of $ \mathop{ (1\ensuremath{-} {M}_{c} \cos \theta )}\nolimits ^{2} $, where ${M}_{c} $ is the Mach number based on the phase velocity ${U}_{c} $ of the convected wave. While the mode $m= 1$ spectrum scales with Strouhal number, suggesting that its energy content is associated with turbulence scales, the axisymmetric mode scales with Helmholtz number – the ratio between source length scale and acoustic wavelength. The axisymmetric radiation has a stronger velocity dependence than the higher-order azimuthal modes, again in agreement with predictions of wavepacket models. We estimate the axial extent of the source of the axisymmetric component of the sound field to be of the order of six to eight jet diameters. This estimate is obtained in two different ways, using, respectively, the directivity shape and the velocity exponent of the sound radiation. The analysis furthermore shows that compressibility plays a significant role in the wavepacket dynamics, even at this low Mach number. Velocity fluctuations on the jet centreline are reduced as the Mach number is increased, an effect that must be accounted for in order to obtain a correct estimation of the velocity dependence of sound radiation. Finally, the higher-order azimuthal modes of the sound field are considered, and a model for the low-angle sound radiation by helical wavepackets is developed. The measured sound for azimuthal modes 1 and 2 at low Strouhal numbers is seen to correspond closely to the predicted directivity shapes.
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14

Kryeziu, O., and E. R. Johnson. "Subsonic to Supersonic Nozzle Flows." SIAM Journal on Applied Mathematics 73, no. 1 (January 2013): 175–94. http://dx.doi.org/10.1137/110845434.

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15

Powell, Alan, and Noel Mascarenhas. "Observations on subsonic edge tones." Journal of the Acoustical Society of America 91, no. 4 (April 1992): 2354. http://dx.doi.org/10.1121/1.403421.

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16

George Bogdan, GHERMAN, FLOREAN Florin, and PORUMBEL Ionut. "Subsonic Jet Pump Comparative Analysis." INCAS BULLETIN 10, no. 1 (March 11, 2018): 73–83. http://dx.doi.org/10.13111/2066-8201.2018.10.1.8.

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17

Stangeby, P. C. "Subsonic and supersonic divertor solutions." Plasma Physics and Controlled Fusion 33, no. 6 (June 1, 1991): 677–83. http://dx.doi.org/10.1088/0741-3335/33/6/008.

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18

Khan, Arroj A., I. Zeba, and M. Jamil. "Subsonic Potentials in Ultradense Plasmas." Zeitschrift für Naturforschung A 74, no. 3 (February 25, 2019): 207–12. http://dx.doi.org/10.1515/zna-2018-0461.

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AbstractThe existence of the subsonic dynamic potential for a test charge in extremely dense quantum plasmas is pointed out for the first time. The dispersion equation of ion acoustic wave in relativistic plasmas is derived by using the quantum hydrodynamic model. The relativistic electrons obey Fermi statistics, whereas the ions are taken classically. The standard model of wake potential is hereafter applied for the derivation of dynamic potential of the test particle. A usual supersonic potential is found suppressed. However, the oscillatory subsonic wake potential does exist in small length scales. The analytical results are applied in different regions by taking the range of magnetic field as well as the electron number density. It is found that the dynamic potential exists only when vt < Cs, showing the presence of subsonic wake potential contrary to the usual supersonic condition vt > Cs. Here vt is the test particle speed and Cs is the acoustic speed defined by the Fermi temperature of the electrons. This work is significant in order to describe the structure formation in the astrophysical environment and laboratory dense plasmas.
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19

Masuda, W., Y. Maeda, and Y. Shirafuji. "Subsonic multiple‐jet aerodynamic window." Review of Scientific Instruments 56, no. 5 (May 1985): 677–81. http://dx.doi.org/10.1063/1.1138203.

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20

ABD-EL-MALEK, MINA. "JOUKOWSKI AIRFOIL IN SUBSONIC FLOW." International Conference on Aerospace Sciences and Aviation Technology 1, CONFERENCE (May 1, 1985): 1–10. http://dx.doi.org/10.21608/asat.1985.26459.

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21

Jones, A. E., K. S. Law, and J. A. Pyle. "Subsonic aircraft and ozone trends." Journal of Atmospheric Chemistry 23, no. 1 (January 1996): 89–105. http://dx.doi.org/10.1007/bf00058706.

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22

Michaels, Paul. "Identification of subsonic P‐waves." GEOPHYSICS 67, no. 3 (May 2002): 909–20. http://dx.doi.org/10.1190/1.1484533.

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A field trial was conducted to test the existence of subsonic (Vp < 331 m/s) P‐waves previously reported in the literature. A 1‐m‐long reverse profile was acquired with three‐component (3C) geophones on a sandy silt (unified classification ML). The silt had a porosity of 54%, a degree of water saturation of 63%, and a plasticity index of 10. No subsonic P‐waves were observed, although high‐frequency (up to 1200 Hz) Rayleigh waves were identified by hodogram analysis. These surface waves were observed with horizontal velocities that varied from 40 to 200 m/s. Hodogram observations and theory suggest that a portion of the data were also in the near‐field.
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23

Loseva, T. V., and I. V. Nemchinov. "Subsonic radiation waves in neon." Soviet Journal of Quantum Electronics 19, no. 2 (February 28, 1989): 221–22. http://dx.doi.org/10.1070/qe1989v019n02abeh007808.

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24

Tesař, Václav. "Characterisation of subsonic axisymmetric nozzles." Chemical Engineering Research and Design 86, no. 11 (November 2008): 1253–62. http://dx.doi.org/10.1016/j.cherd.2008.04.012.

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25

Sahu, Rishabh Kumar, Saurabh Sharma, and Vivek Swaroop Vishal Kumar. "Experimental Investigations and Computational Analysis on Subsonic Wind Tunnel." International Journal of Trend in Scientific Research and Development Volume-3, Issue-3 (April 30, 2019): 1708–11. http://dx.doi.org/10.31142/ijtsrd23511.

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26

Chi, R. M., and A. V. Srinivasan. "Some Recent Advances in the Understanding and Prediction of Turbomachine Subsonic Stall Flutter." Journal of Engineering for Gas Turbines and Power 107, no. 2 (April 1, 1985): 408–17. http://dx.doi.org/10.1115/1.3239741.

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In this paper, some recent advances in the understanding and prediction of subsonic flutter of jet engine fan rotor blades are reviewed. Among the topics discussed are (i) the experimental evidence of mistuning in flutter responses, (ii) new and promising unsteady aerodynamic models for subsonic stall flutter prediction, (iii) an overview of flutter prediction methodologies, and (iv) a new research effort directed toward understanding the mistuning effect on subsonic stall flutter of shrouded fans. A particular shrouded fan of advanced design is examined in the detailed technical discussion.
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27

MANKBADI, REDA R., and AMR A. ALI. "EVALUATION OF SUBSONIC INFLOW TREATMENTS FOR UNSTEADY JET FLOW." Journal of Computational Acoustics 07, no. 03 (September 1999): 147–60. http://dx.doi.org/10.1142/s0218396x99000114.

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Linearized Euler simulations of the unsteady flow of a subsonic jet and its associated acoustic field are presented in this paper. Various subsonic inflow treatments are evaluated. Some of these treatments have been found to produce reflections at the inflow while others are reflection-free. Results are then presented for the effect of Mach number on the radiated sound. It is shown that as the Mach number increases the source becomes noncompact and the directivity is characterized by a well-defined peak. By comparing the linear prediction to the experimental results, validity range of linear approximation for subsonic jet noise is assessed.
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28

GU, Xumin, and Tian-Yi WANG. "On subsonic and subsonic-sonic flows in the infinity long nozzle with general conservatives force." Acta Mathematica Scientia 37, no. 3 (May 2017): 752–67. http://dx.doi.org/10.1016/s0252-9602(17)30035-8.

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29

Stenke, A., V. Grewe, and S. Pechtl. "Do supersonic aircraft avoid contrails?" Atmospheric Chemistry and Physics Discussions 7, no. 5 (September 4, 2007): 12927–58. http://dx.doi.org/10.5194/acpd-7-12927-2007.

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Abstract. The impact of a potential future fleet of supersonic aircraft on contrail coverage and contrail radiative forcing is investigated by means of simulations with the general circulation model ECHAM4.L39(DLR) including a contrail parameterization. The model simulations consider air traffic inventories of a subsonic fleet and of a combined fleet of sub- and supersonic aircraft for the years 2025 and 2050, respectively. In case of the combined fleet, part of the subsonic fleet is replaced by supersonic aircraft. Supersonic aircraft fly at higher cruise levels (18 to 20 km) than subsonic aircraft (10 to 12 km). The different ambient meteorological conditions in terms of temperature and humidity affect the formation of contrails. At subsonic cruise levels, the combined air traffic scenario reveals a reduction in contrail cover in northern extratropics, especially over the North Atlantic and Pacific. At supersonic flight levels, contrail formation is mainly restricted to tropical regions. The northern extratropical stratosphere is only in winter cold enough for the formation of contrails. Total contrail coverage is only marginally affected by the shift in flight altitude. The model simulations indicate a global annual mean contrail cover of 0.372% for the subsonic and 0.366% for the combined fleet in 2050, respectively. The simulated contrail radiative forcing is most closely correlated to the total contrail cover, although contrails in the tropical lower stratosphere are found to be optically thinner than contrails in the extratropical upper troposphere. The global annual mean contrail radiative forcing in 2050 (2025) amounts to 24.7 mW m−2 (9.4 mW m−2) for the subsonic fleet and 24.2 mW m−2 (9.3 mW m−2) for the combined fleet. A reduced supersonic cruise speed (Mach 1.6 instead of Mach 2.0) leads to a downward shift in contrail cover, but does not affect global mean total contrail cover and contrail radiative forcing. Hence the partial substitution of subsonic air traffic leads to a shift of contrail occurrence from mid to low latitudes, but the resulting change in contrail-induced climate impact is almost negligible.
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30

Behn, Chris, and M. Marder. "The transition from subsonic to supersonic cracks." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 373, no. 2038 (March 28, 2015): 20140122. http://dx.doi.org/10.1098/rsta.2014.0122.

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We present the full analytical solution for steady-state in-plane crack motion in a brittle triangular lattice. This allows quick numerical evaluation of solutions for very large systems, facilitating comparisons with continuum fracture theory. Cracks that propagate faster than the Rayleigh wave speed have been thought to be forbidden in the continuum theory, but clearly exist in lattice systems. Using our analytical methods, we examine in detail the motion of atoms around a crack tip as crack speed changes from subsonic to supersonic. Subsonic cracks feature displacement fields consistent with a stress intensity factor. For supersonic cracks, the stress intensity factor disappears. Subsonic cracks are characterized by small-amplitude, high-frequency oscillations in the vertical displacement of an atom along the crack line, while supersonic cracks have large-amplitude, low-frequency oscillations. Thus, while supersonic cracks are no less physical than subsonic cracks, the connection between microscopic and macroscopic behaviour must be made in a different way. This is one reason supersonic cracks in tension had been thought not to exist.
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31

Kuznetsov, Sergey V. "Subsonic Lamb Waves in Anisotropic Plates." International Journal for Multiscale Computational Engineering 2, no. 3 (2004): 477–86. http://dx.doi.org/10.1615/intjmultcompeng.v2.i3.80.

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32

Nguyen, T. T., and A. R. Karagozian. "Liquid fuel jet in subsonic crossflow." Journal of Propulsion and Power 8, no. 1 (January 1992): 21–29. http://dx.doi.org/10.2514/3.23437.

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33

Sher, E., and T. Bar-Kohany. "SUBSONIC EFFERVESCENT ATOMIZATION: A THEORETICAL APPROACH." Atomization and Sprays 14, no. 6 (2004): 495–510. http://dx.doi.org/10.1615/atomizspr.v14.i6.10.

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34

Richarz, W. G. "Fine structure of subsonic jet noise." AIAA Journal 24, no. 5 (May 1986): 849–50. http://dx.doi.org/10.2514/3.9354.

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35

Brocher, Eric, and Elisabeth Duport. "Resonance tubes in a subsonic flowfield." AIAA Journal 26, no. 5 (May 1988): 548–52. http://dx.doi.org/10.2514/3.9932.

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36

Kearney-Fischer, M., A. Sinha, and M. Samimy. "Intermittent Nature of Subsonic Jet Noise." AIAA Journal 51, no. 5 (May 2013): 1142–55. http://dx.doi.org/10.2514/1.j051930.

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37

German, Brian J. "Laplacian Equivalents to Subsonic Potential Flows." AIAA Journal 47, no. 1 (January 2009): 129–41. http://dx.doi.org/10.2514/1.36877.

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38

Udin, Sergei V., and William J. Anderson. "Wing mass formula for subsonic aircraft." Journal of Aircraft 29, no. 4 (July 1992): 725–27. http://dx.doi.org/10.2514/3.46232.

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39

Kuznetsov, S. V. "Subsonic lamb waves in anisotropic layers." Journal of Applied Mathematics and Mechanics 65, no. 2 (January 2001): 291–99. http://dx.doi.org/10.1016/s0021-8928(01)00033-8.

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40

Henderson, J., K. J. Badcock, and B. E. Richards. "Understanding subsonic and transonic cavity flows." Aeronautical Journal 105, no. 1044 (February 2001): 77–84. http://dx.doi.org/10.1017/s0001924000011520.

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AbstractA computational investigation of the subsonic and transonic turbulent open flow over cavities was conducted. Simulations of these oscillatory flows were generated through time-accurate solutions of the Reynolds-averaged form of the Navier-Stokes equations. The effect of turbulence was included through the k–ω model. The results presented include calculations of the acoustic pressure distributions along the cavity floor, which compare well with experiment. The results are then used to describe the behaviour of the flow.
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41

Vuorinen, Ville, Armin Wehrfritz, Jingzhou Yu, Ossi Kaario, Martti Larmi, and Bendiks Jan Boersma. "Large-Eddy Simulation of Subsonic Jets." Journal of Physics: Conference Series 318, no. 3 (December 22, 2011): 032052. http://dx.doi.org/10.1088/1742-6596/318/3/032052.

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42

Busse, C. A., and R. I. Loehrke. "Subsonic Pressure Recovery in Cylindrical Condensers." Journal of Heat Transfer 111, no. 2 (May 1, 1989): 533–37. http://dx.doi.org/10.1115/1.3250710.

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A method is presented for predicting laminar, subsonic flow in axisymmetric cylindrical heat pipe condensers. The method involves the use of the boundary layer approximation and a noncontinuous power series to describe the velocity profile under conditions including strong axial flow reversal. A comparison between laminar predictions and measurements indicates that transition to turbulent flow in the condenser begins when the absolute value of the radial Reynolds number exceeds 6. The condenser pressure recovery in the turbulent regime can be calculated from the momentum flow at the condenser inlet and an empirical wall-friction parameter.
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43

Razani, A. "Subsonic detonation waves in porous media." Physica Scripta 94, no. 8 (May 23, 2019): 085209. http://dx.doi.org/10.1088/1402-4896/ab029b.

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44

Aniskin, V. M., D. A. Bountin, A. A. Maslov, S. G. Mironov, and I. S. Tsyryul’nikov. "Stability of a subsonic gas microjet." Technical Physics 57, no. 2 (February 2012): 174–80. http://dx.doi.org/10.1134/s106378421202003x.

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45

Srinivasan, K., and E. Rathakrishnan. "Morphology of subsonic rectangular slot jets." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 222, no. 4 (April 2008): 449–61. http://dx.doi.org/10.1243/09544100jaero281.

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46

Feimin, Huang, Tianyi Wang, and Yong Wang. "On multi-dimensional sonic-subsonic flow." Acta Mathematica Scientia 31, no. 6 (November 2011): 2131–40. http://dx.doi.org/10.1016/s0252-9602(11)60389-5.

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47

Lazarian, A., and Thiem Hoang. "Subsonic Mechanical Alignment of Irregular Grains." Astrophysical Journal 669, no. 2 (October 16, 2007): L77—L80. http://dx.doi.org/10.1086/523849.

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48

DOSHIDA, Minoru, and Hiroshi HARA. "A N2/CO2 subsonic mixing laser." Review of Laser Engineering 17, no. 9 (1989): 635–41. http://dx.doi.org/10.2184/lsj.17.9_635.

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49

Mascarenhas, Noel, and Alan Powell. "Observations on subsonic edge tones, continued." Journal of the Acoustical Society of America 92, no. 4 (October 1992): 2309–10. http://dx.doi.org/10.1121/1.405100.

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50

Chong, Xie. "Subsonic choked flow in the microchannel." Physics of Fluids 18, no. 12 (December 2006): 127104. http://dx.doi.org/10.1063/1.2408510.

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