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Journal articles on the topic 'Supersonic nozzle'

Author: Grafiati

Published: 4 June 2021

Last updated: 18 June 2025

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1

Sharapov, Serhii, Danylo Husiev, Volodymyr Klymenko, et al. "Thermophysical Modeling of the Vaporization Process in a Motive Nozzle with a Profiled Supersonic Part." Energies 17, no. 24 (2024): 6465. https://doi.org/10.3390/en17246465.

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In this article, thermophysical modeling of boiling flows in the motive nozzle is carried out for a liquid–vapor jet apparatus (LVJA). Existing thermophysical models make it possible to calculate nozzles, which, in their shape, are close to Laval nozzles. They also allow for determining the position of the outlet cross-sectional area of the nozzle, where the flow separation from the channel walls occurs. However, these models do not allow for profiling the nozzle’s supersonic part, which does not make it possible to ensure the maximum efficiency of the vaporization process. Therefore, in the p

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2

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 atmospher

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3

Veeresh Kumar, G., M. Naga Sailaja, and Ravi Sandeep Kumar Kona. "Testing of a Supersonic Nozzle with Supersonic Intake." International Journal of Science and Research (IJSR) 10, no. 9 (2021): 1522–24. https://doi.org/10.21275/sr21713140558.

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4

Kumar, Bholu, Suresh Kant Verma, and Shantanu Srivastava. "Mixing Characteristics of Supersonic Jet from Bevelled Nozzles." International Journal of Heat and Technology 39, no. 2 (2021): 559–72. http://dx.doi.org/10.18280/ijht.390226.

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The present study focuses on the effect of nozzle exit inclination on the mixing characteristics of Mach 2.17 overexpanded jets at the NPR 5, NPR 6 and NPR 7, using commercial software package ANSYS Fluent. The convergent-divergent nozzles, investigated are circular nozzle and bevel nozzle with bevel angle 300, and bevel angel 450. The nozzles are constructed with equal throat-to-exit area ratio, in order to maintain uniform Mach number at the nozzle exit. From the results, it was found that, the bevelled nozzles effectively reduce the jet core as much as 46%, indicating enhanced jet mixing. I

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5

Haque, S., S. Matsuo, and H. Kaeriyama. "Characteristics of non-equilibrium condensing flow in three-dimensional supersonic rectangular nozzles." Journal of Physics: Conference Series 2217, no. 1 (2022): 012087. http://dx.doi.org/10.1088/1742-6596/2217/1/012087.

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Abstract Fluid flow inside a supersonic nozzle with a rectangular cross-section induces secondary flow due to the shape of the upper wall curvature. The secondary flow forms longitudinal vortices near the wall of the nozzle corner which destabilizes the nozzle outlet flow due to the early transition of the flow from laminar to turbulent. It is known that non-equilibrium homogeneous condensation occurs in a supersonic rectangular nozzle due to the rapid expansion of the condensable fluid with large latent heat such as water vapor. Homogeneous condensation takes place through the formation of wa

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6

HAIF, Sidali, Hakim KBAB, and Amina BENKHEDDA. "Altitude-compensating axisymmetric supersonic nozzle design and flow analysis." INCAS BULLETIN 15, no. 2 (2023): 33–47. http://dx.doi.org/10.13111/2066-8201.2023.15.2.4.

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Altitude-adapted nozzles are designed to facilitate flow adaptation during rocket ascent in the atmosphere, without requiring mechanical activation. As a consequence, the performance of the nozzle is significantly improved. The aim of this study is to develop a new profile of axisymmetric supersonic nozzles adapted at altitude (Dual Bell Nozzle with Central Body), which is characterized by an E-D nozzle as a basic profile. The performances obtained for this nozzle (E-D Nozzle) are then compared to those of a Plug nozzle. The E-D nozzle shows significant performance advantages over the Plug noz

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7

Ternova, K. V. "Effect of the length of truncated nozzle with a tip on its thrust characteristics." Technical mechanics 2022, no. 4 (2022): 26–34. http://dx.doi.org/10.15407/itm2022.04.026.

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Nowadays, for solving new problems, rocket engine nozzle developers are increasingly turning to non- traditional nozzle configurations that differ from the classic Laval one. A relatively new line in the design of supersonic nozzles is the development of the so-called bell-shaped nozzle, which, unlike the classical Laval nozzle, has a larger angle of entry into the supersonic part of the nozzle. In this case, dual bell nozzles, which have two flow expansion sections in their supersonic part, are considered. However, the effect of the length ratio of the two flow expansion sections of a truncat

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8

Hamaidia, Walid, Toufik Zebbiche, Mohamed Sellam, and Abderrazak Allali. "Performance improvement of supersonic nozzles design using a high-temperature model." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 13 (2019): 4895–910. http://dx.doi.org/10.1177/0954410019831862.

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The aim of this paper is to discuss the development of new contours of axisymmetric supersonic nozzles giving a uniform and parallel flow at the exit section, to improve the aerodynamic performances compared to the minimum length nozzle, by increasing the exit Mach number and the thrust coefficient, and by reduction of the nozzle's mass, while holding the same throat section between the two nozzles. The new nozzle is named the best performance nozzle. Its form contains a cylindrical central body and an external wall for the flow redress. The study is done at high temperature, lower than the di

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9

Zhang, Tian, Deji Jing, Shaocheng Ge, Jiren Wang, Xi Chen, and ShuaiShuai Ren. "Dust removal characteristics of a supersonic antigravity siphon atomization nozzle." Advances in Mechanical Engineering 12, no. 12 (2020): 168781402097768. http://dx.doi.org/10.1177/1687814020977689.

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To improve the trapping efficiency of respiratory dust by aerodynamic atomization, reduce the energy consumption and the requirements for the working conditions of nozzles and maintain the health and safety of workers, a comparative experiment evaluating aerodynamic atomization dust removal characteristics was conducted with a self-developed supersonic siphon atomization nozzle, which utilizes a Laval nozzle as the core, and an existing ultrasonic atomization nozzle. The experimental results showed that the new type of nozzle, from the perspectives of droplet speed, conservation of water and p

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10

Resta, Emanuele, Roberto Marsilio, and Michele Ferlauto. "Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method." Fluids 6, no. 12 (2021): 441. http://dx.doi.org/10.3390/fluids6120441.

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The application of the Shock Vector Control (SVC) approach to an axysimmetric supersonic nozzle is studied numerically. SVC is a Fluidic Thrust Vectoring (FTV) strategy that is applied to fixed nozzles in order to realize jet-vectoring effects normally obtained by deflecting movable nozzles. In the SVC method, a secondary air flow injection close to the nozzle exit generates an asymmetry in the wall pressure distribution and side-loads on the nozzle, which are also lateral components of the thrust vector. SVC forcing of the axisymmetric nozzle generates fully three-dimensional flows with very

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11

Han, S. Y., R. R. Taghavi, and S. Farokhi. "Numerical simulation of supersonic jet instability modes of plane and notched rectangular nozzles." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 226, no. 1 (2011): 104–22. http://dx.doi.org/10.1177/0954406211413964.

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The effect of exit geometry of a rectangular nozzle on the instability modes and mixing characteristics of under-expanded supersonic jets is computationally investigated. The unsteady three-dimensional viscous simulation is based on the Proteus code developed at NASA Glenn Research Center. A shock adaptive grid generator was developed to enhance the shock simulation. The nozzle aspect ratio for both plane and notched rectangular nozzles in this study is 5.0 and the fully expanded jet Mach number is 1.526. For the case of a plane rectangular nozzle, the ‘flapping’ oscillations, which are extens

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12

Shourehdeli, Shaban Alyari, Kamran Mobini, and Ali Asakereh. "Numerical Investigation of the Effects of Primary Nozzle Diverging Portion on Performance of the Supersonic Ejector of an Ejector Refrigeration Cycle." International Journal of Air-Conditioning and Refrigeration 27, no. 03 (2019): 1950030. http://dx.doi.org/10.1142/s2010132519500305.

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A supersonic ejector with desirable performance characteristics reduces the energy consumption rate of an ejector refrigeration system and increases its coefficient of performance (COP). In this paper, the effects of using different primary nozzles on the performance of a supersonic ejector of an ejector refrigeration system have been numerically studied, while the working fluid is steam. To this end, conical, Rao and parallel-flow primary nozzles with identical converging portions and equal exit area to throat area ratios have been tested. The diverging portion curves for the parallel-flow an

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13

Maeda, Hiroaki, Hikaru Fukuda, Shinichiro Nakao, Yoshiaki Miyazato, and Yojiro Ishino. "Rainbow schlieren measurements in underexpanded jets from square supersonic micro nozzles." EPJ Web of Conferences 180 (2018): 02058. http://dx.doi.org/10.1051/epjconf/201818002058.

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The slightly underexpanded free jet issued from a supersonic micro nozzle with a design Mach number of 1.5 and a square shape of 1 mm × 1 mm at the nozzle exit has been experimentally investigated using the rainbow schlieren deflectometry combined with the computed tomography where the nozzle operating pressure ratio is held constant at 4.0. Density fields in the free jet obtained from the rainbow schlieren deflectometry are the vortex sheet theory proposed by Tam. It is shown that there is good quantitative agreement between experiment and theory. It is shown that the rainbow schlieren deflec

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14

Ternova, K. V., N. P. Syrotkina, and L. V. Muzyka. "Effect of the throat geometry on the flow in a supersonic round nozzle." Technical mechanics 2024, no. 4 (2024): 31–40. https://doi.org/10.15407/itm2024.04.031.

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The goal of this work was to analyze the effect of the corner point of the rocket engine nozzle contour on the nozzle flow characteristics. A two-phase flow in third rocket stage nozzles of different contours was considered. The site of condensed phase deposition onto the wall of a nozzle with an acute angle in the critical area was determined. Rounding the corner point at the supersonic area inlet changed the particle trajectory. The rounding radius best in terms of deposition reduction was found. A comparison showed that, despite the different profiles, the specific impulses of these nozzles

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15

Qurooni, Faisal Al, Ali Vakil, Ehab Elsaadawy, and Sheldon I. Green. "Numerical simulation of an over-expanded supersonic and subsonic industrial nozzle flow relevant to flaring system." Transactions of the Canadian Society for Mechanical Engineering 43, no. 4 (2019): 471–80. http://dx.doi.org/10.1139/tcsme-2018-0230.

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Flaring in oil and gas production is the controlled burning of unwanted exhaust gases to enhance safety. To improve flare combustion, gas flares are equipped with air nozzles that introduce extra oxygen and improve mixing in the combustion zone. These nozzles are operated in the subsonic, sonic, or supersonic regimes. In this paper, we are concerned with turbulence modeling of the jet flow exiting from a particular convergent–divergent nozzle used in flare systems. That nozzle has convergent and divergent sections that are connected via a throat section with a finite length and constant diamet

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16

Ternova, K. V. "Effect of the tip geometry of a truncated supersonic nozzle on its characteristics." Technical mechanics 2023, no. 2 (2023): 32–40. http://dx.doi.org/10.15407/itm2023.02.032.

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Truncated nozzles are used for tight packing of the rocket engine. Such nozzles have a profiled tip to maximize the filling of space and reduce the overall weight. This paper is concerned with the study the effect of the tip geometry of a truncated supersonic nozzle on its characteristics. The features of the gas flow at different initial pressures and different environmental conditions in the supersonic area of a nozzle with a bell-shaped tip of different lengths are considered. The flow inside the nozzle followed by the jet outflow into the surrounding space was simulated. The flow simulatio

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17

Yuan, Run, Bo Yang, Hong Yan Ruan, and Xiao Wang. "Flow Field Analysis of Gas Jets from Nozzles for Gas-Assisted Laser Cutting." Key Engineering Materials 419-420 (October 2009): 409–12. http://dx.doi.org/10.4028/www.scientific.net/kem.419-420.409.

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The gas jets from the conical and new designed supersonic nozzles on different working pressure are simulated by a computational fluid dynamics code, FLUENT, using standard k-ε model and unstructured grid finite volume method with compressible axis-symmetry N-S equation. Under the same condition of pressure-inlet, the distribution of symmetry velocity and that of static pressure are compared. The result of the analysis indicates that conical nozzle outlet can reach subsonic or sonic flow. It is fit for low speed and low pressure situation. The gas jet from the new design supersonic nozzle work

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18

Kateryna, Ternova, and Syrotkina Nataliya. "Regression analysis of impulse characteristics shorted supersonic nozzle." System technologies 3, no. 146 (2023): 3–9. http://dx.doi.org/10.34185/1562-9945-3-146-2023-01.

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When designing and testing rocket engines, an important problem is the choice of the contour of the supersonic part of the nozzle. Recently, with the development of rock-et and space technology, different contours of nozzles have appeared that meet new tasks, requirements for the density of the layout, the need to increase the momentum co-efficient, accounting for various operating conditions, etc. Therefore, the relevance of the work is determined by the need to choose the contour of the supersonic part of the nozzle to increase the impulse characteristics of the flow in the shortened nozzle.

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19

Pryadko, N. S., H. O. Strelnikov, and K. V. Ternova. "RESEARCH OF SUPERSONIC FLOW IN SHORTENED NOZZLES OF ROCKET ENGINES WITH A BELL-SHAPED TIP." Kosmìčna nauka ì tehnologìâ 30, no. 1 (2024): 03–13. http://dx.doi.org/10.15407/knit2024.01.003.

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The flow in a shortened nozzle with a bell-shaped tip is considered. A comparison of the wave structures of the supersonic gas flow in shortened nozzles with short and long tips formed by compression and stretching of the original bell-shaped nozzle for connection, respectively, with the long and short conical part of the base nozzle at the same nozzle length was carried out. Under operation conditions at sea level and low pressure at the nozzle inlet (P0<50·105 Ра), a large-scale vortex structure, starting from the corner point of the nozzle inlet, is observed in both nozzles. In addition,

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20

Liu, Xiao Bo, and Yong Xue Li. "Numerical Simulation on Fluid Field of Different Structure Supersonic Atomizing Nozzle." Advanced Materials Research 268-270 (July 2011): 869–74. http://dx.doi.org/10.4028/www.scientific.net/amr.268-270.869.

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A supersonic atomizing nozzle is the quite vital component in manufacturing superfine copper powders. The performances of the nozzle have a extremely major influence on the properties of copper powders. Base on the manufacturing technological conditions and the structural features of supersonic nozzle, the mathematical models of fluid field in the supersonic nozzle can be established. According to the method of computational fluid dynamics, the control equation is dispersed. The gridding is created by the means of free division. The finite element equations are set up by Galerkin. Then the imp

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21

A.K., Mubarak, and Tide P.S. "Design of a double parabolic supersonic nozzle and performance evaluation by experimental and numerical methods." Aircraft Engineering and Aerospace Technology 91, no. 1 (2018): 145–56. http://dx.doi.org/10.1108/aeat-12-2017-0275.

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Purpose The purpose of this paper is to design a double parabolic nozzle and to compare the performance with conventional nozzle designs. Design/methodology/approach The throat diameter and divergent length for Conical, Bell and Double Parabolic nozzles were kept same for the sake of comparison. The double parabolic nozzle has been designed in such a way that the maximum slope of the divergent curve is taken as one-third of the Prandtl Meyer (PM) angle. The studies were carried out at Nozzle Pressure Ratio (NPR) of 5 and also at design conditions (NPR = 3.7). Experimental measurements were car

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22

MOHANTA, Prasanta Kumar, and B. T. N. SRIDHAR. "Effect of Hydraulic Diameter on Potential Core Decay of Supersonic Jets." INCAS BULLETIN 12, no. 1 (2020): 119–26. http://dx.doi.org/10.13111/2066-8201.2020.12.1.11.

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Various studies dealing with decay characteristics of circular and noncircular supersonic jets were conducted by previous researchers. But in these studies due emphasis was not given to the hydraulic diameter (Dh), shape factor (ζ) & the nozzle lip parameters which have significant impact on the characteristics of noncircular supersonic jet. In this study, it has been shown that these parameters played a significant role on supersonic core decay characteristics [2, 3, 6] of the jet. The scope of this study included supersonic core length (Lc), decay pattern, due to noncircular shaped nozzl

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23

Lee, Ji-A., Chang-Su Ha, and Jeong-Whan Han. "Effect of Supersonic Oxygen Lance on Post-Combustion in Converter Steelmaking Process – Experiment and Analysis with Converter Simulator." Korean Journal of Metals and Materials 61, no. 7 (2023): 514–23. http://dx.doi.org/10.3365/kjmm.2023.61.7.514.

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Employing post-combustion technology in the converter, using the sensible heat of the hot metal and the oxidation reaction heat as a heat source, is known to compensate for insufficient heat in the converter process. However, most studies on post-combustion have been conducted using subsonic nozzles, whereas actual converter processes use supersonic nozzles. Therefore, research on the combustion behavior of supersonic jets is needed. In this study, experiments and analyses were conducted using a converter simulator and a supersonic nozzle to investigate the effect of nozzle height on the post-

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24

Powers, Russell W., and Dennis K. McLaughlin. "Acoustics measurements of military-style supersonic beveled nozzle jets with interior corrugations." International Journal of Aeroacoustics 16, no. 1-2 (2016): 21–43. http://dx.doi.org/10.1177/1475472x16680446.

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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

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25

Tillman, T. G., R. W. Paterson, and W. M. Presz. "Supersonic nozzle mixer ejector." Journal of Propulsion and Power 8, no. 2 (1992): 513–19. http://dx.doi.org/10.2514/3.23506.

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26

Lloyd, Daniel L., and Richard J. Madlener. "Noise attenuating supersonic nozzle." Journal of the Acoustical Society of America 91, no. 5 (1992): 3085. http://dx.doi.org/10.1121/1.402892.

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27

Dutton, J. C. "Swirling supersonic nozzle flow." Journal of Propulsion and Power 3, no. 4 (1987): 342–49. http://dx.doi.org/10.2514/3.22996.

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28

Wu, Lian Sheng, Guang Li Li, and Qi Fu. "The Study of Design and Installation Process for Supersonic Nozzle." Advanced Materials Research 569 (September 2012): 500–503. http://dx.doi.org/10.4028/www.scientific.net/amr.569.500.

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A practical optimal design method of supersonic nozzle is proposed for a supersonic wind tunnel’s design. Design a set of nozzle wall lines with the same nozzle length and different Mach numbers 1.5, 2.0, 2.5. Use numerical simulation method for the verify and analysis of the designed nozzle. Mainly study the impact of the installation gradient between nozzle and test section on flow field quality. This wind tunnel is the subsonic, transonic and supersonic wind tunnel and its test section cross is 0.2 m × 0.2 m .The impact on flow field quality of the test section was studied quantitatively by

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29

Palacio, Jose Alfredo, Ivan Patino, and William Orozco. "Influence of the ratio of nozzle inlet to nozzle throat areas on the performance of a jet pump for vacuum applications using computational fluid dynamics." AIUB Journal of Science and Engineering (AJSE) 22, no. 3 (2023): 214–22. http://dx.doi.org/10.53799/ajse.v22i3.489.

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The nozzle design is one of the most important issues because it determines the pressure range and the other dimensions to guarantee an adequate performance of a jet_pump. An incorrect design of this part can cause shock waves and unnecessary overexpansion of the power fluid. The nozzle’s main purpose is to allow the high-pressure, low-velocity primary fluid to be accelerated in such a way as to substantially decrease the fluid pressure while increasing its velocity. This is achieved because the subsonic flow accelerates when entering the convergent part of the nozzle, obtaining a sonic or sup

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30

Guram, Sejal, Vidhanshu Jadhav, Prasad Sawant, and Ankit Kumar Mishra. "Review Study on Thermal Characteristics of Bell Nozzle used in Supersonic Engine." 1 2, no. 1 (2023): 4–14. http://dx.doi.org/10.46632/jame/2/1/2.

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The nozzle is an important component of the rocket motor system, and a rocket’s overall performance is highly reliant on its aerodynamic design. The nozzle contour can be meticulously shaped to improve performance significantly. The design and shape of rocket nozzles have evolved over the last several decades as a result of extensive research. The nozzle design is composed of two components, an integrated throat, an entry and an exit cone, and a thermal protection system. The Bell Nozzle is designed to provide clearance space for placing the ITE and exit cone, with a cone inflection angle of 1

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31

Dubrovskyi, Ivan. "Результати проектування надзвукового сопла з подвійним розширенням для рідинного ракетного двигуна першого ступеня методами обчислювального аналізу". Aerospace Technic and Technology, № 6 (6 грудня 2023): 14–21. http://dx.doi.org/10.32620/aktt.2023.6.02.

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The subject of this study is dual-bell supersonic nozzles of liquid rocket engines. The goal is to design a dual-bell supersonic nozzle that will provide maximum thrust for a liquid rocket engine in the first stage of a launch vehicle by solving an optimization problem using numerical simulation methods. The goal of the study is to choose the exit pressures of each part of the dual-bell nozzle based on the known flight trajectory of the launch vehicle, set and solve the problem of optimizing the dual-bell nozzle contour, and assess the impact of the use of a dual-bell nozzle on the efficiency

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32

Zhang, Tian, Deji Jing, Shaocheng Ge, Jiren Wang, Xiangxi Meng, and ShuaiShuai Ren. "Numerical simulation of the dimensional transformation of atomization in a supersonic aerodynamic atomization dust-removing nozzle based on transonic speed compressible flow." International Journal of Coal Science & Technology 7, no. 3 (2020): 597–610. http://dx.doi.org/10.1007/s40789-020-00314-3.

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Abstract To simulate the transonic atomization jet process in Laval nozzles, to test the law of droplet atomization and distribution, to find a method of supersonic atomization for dust-removing nozzles, and to improve nozzle efficiency, the finite element method has been used in this study based on the COMSOL computational fluid dynamics module. The study results showed that the process cannot be realized alone under the two-dimensional axisymmetric, three-dimensional and three-dimensional symmetric models, but it can be calculated with the transformation dimension method, which uses the para

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33

MOASE, WILLIAM H., MICHAEL J. BREAR, and CHRIS MANZIE. "The forced response of choked nozzles and supersonic diffusers." Journal of Fluid Mechanics 585 (August 7, 2007): 281–304. http://dx.doi.org/10.1017/s0022112007006647.

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The response of choked nozzles and supersonic diffusers to one-dimensional flow perturbations is investigated. Following previous arguments in the literature, small flow perturbations in a duct of spatially linear steady velocity distribution are determined by solution of a hyper-geometric differential equation. A set of boundary conditions is then developed that extends the existing work to a nozzle of arbitrary geometry. This analysis accommodates the motion of a plane shock wave and makes no assumption about the nozzle compactness. Numerical simulations of the unsteady, quasi-one-dimensiona

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34

Bhide, Kalyani, Kiran Siddappaji, and Shaaban Abdallah. "Aspect Ratio Driven Relationship between Nozzle Internal Flow and Supersonic Jet Mixing." Aerospace 8, no. 3 (2021): 78. http://dx.doi.org/10.3390/aerospace8030078.

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This work attempts to connect internal flow to the exit flow and supersonic jet mixing in rectangular nozzles with low to high aspect ratios (AR). A series of low and high aspect ratio rectangular nozzles (design Mach number = 1.5) with sharp throats are numerically investigated using steady state Reynolds-averaged Navier−Stokes (RANS) computational fluid dynamics (CFD) with k-omega shear stress transport (SST) turbulence model. The numerical shadowgraph reveals stronger shocks at low ARs which become weaker with increasing AR due to less flow turning at the throat. Stronger shocks cause more

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35

Ihnatiev, O. D., N. S. Pryadko, G. O. Strelnikov, and K. V. Ternova. "Gas flow in a truncated Laval nozzle with a bell-shaped tip." Technical mechanics 2022, no. 2 (2022): 39–46. http://dx.doi.org/10.15407/itm2022.02.039.

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Flow in a truncated supersonic Laval nozzle with a bell-shaped tip (“bell”) is investigated. This nozzle configuration can be used in tight layouts of multistage rockets of short length with improved energy-mass characteristics. Similar types of nozzles were developed at the Institute of Technical Mechanics of the National Academy of Sciences and the State Space Agency of Ukraine in the 1990s. Using approximate methods, the parameters of variously configured truncated nozzles were calculated, and their models were made. Some of the models were blown with cold air, and their characteristics wer

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36

Dehane, Rabie, Khatir Naima, Abdelkrim Liazid, et al. "Impact of the convergent geometric profile on boundary layer separation in the supersonic over-expanded nozzle." Open Physics 20, no. 1 (2022): 1080–95. http://dx.doi.org/10.1515/phys-2022-0185.

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Abstract This article aims to conduct a numerical investigation of phenomena induced by gas expansion in chemical propulsion nozzles. A numerical simulation of full-scale flat convergent-divergent nozzle geometry using the finite volume method on structured meshes is performed to predict the change in the convergent geometry on the boundary layer separation resulting from a shock/shock and shock/boundary layer. Two turbulence models are tested, namely, the k−ε and k−ω shear-stress transport (SST) models. Three steps are considered to achieve this work. First, 10 numerical schemes are tested to

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37

Vasyliv, S. S., and H. O. Strelnykov. "Rocket engine thrust vector control by detonation product injection into the supersonic portion of the nozzle." Technical mechanics 2020, no. 4 (2020): 29–34. http://dx.doi.org/10.15407/itm2020.04.029.

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For solving non-traditional problems of rocket flight control, in particular, for the conditions of impact of a nuclear explosion, non-traditional approaches to the organization of the thrust vector control of a rocket engine are required. Various schemes of gas-dynamic thrust vector control systems that counteract impact actions on the rocket were studied. It was found that the dynamic characteristics of traditional gas-dynamic thrust vector control systems do not allow one to solve the problem of counteracting impact actions on the rocket. Appropriate dynamic characteristics can provide a pe

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Flock, Andreas K., and Ali Gülhan. "Design of converging-diverging nozzles with constant-radius centerbody." CEAS Space Journal 12, no. 2 (2019): 191–201. http://dx.doi.org/10.1007/s12567-019-00286-4.

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AbstractSeveral flow phenomena, such as recirculating wake flows or noise generation, occur in aerodynamic configurations with backward facing steps. In this context, subsonic nozzles with constant-radius centerbodies exist, which enable fundamental research of these phenomena for $$M < 1$$M<1. For the supersonic regime, however, the existing database and knowledge are limited. Therefore, this work presents a design approach for a converging-diverging nozzle with constant-radius centerbody. For the nozzle throat, Sauer’s method is modified to include a centerbody. The method of character

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ABADA, O., H. KBAB, and S. HAIF. "Optimizing the design of a supersonic Planar Dual Bell Nozzle (PDBN)." Kosmìčna nauka ì tehnologìâ 30, no. 2 (2024): 15–27. http://dx.doi.org/10.15407/knit2024.02.015.

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Dual bell nozzles present a promising solution for maximizing propulsion efficiency at high altitudes, while also mitigating dangerous side loads at lower altitudes. Such nozzles are comprised of two distinct contours, with the first optimized for low altitude operation, and the second tailored for high altitude conditions. These contours are interconnected at an inflexion point. The present study focuses on optimizing the contour design of a planar dual bell nozzle. Leveraging the commercial ANSYS-Fluent software, we conducted an investigation into the influence of the inflection angle on the

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Zhu, Meijun, Lei Fu, Shuai Zhang, and Yao Zheng. "Design and optimization of three-dimensional supersonic asymmetric truncated nozzle." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 15 (2017): 2923–35. http://dx.doi.org/10.1177/0954410017718567.

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Three-dimensional supersonic nozzle is an important component of air-breathing hypersonic vehicles to produce thrust and lift force. Since the length of nozzle with ideal design is too long to meet the trim requirements of integrated air-breathing hypersonic vehicles, it is necessary to design a truncated nozzle to provide excellent aerodynamic performance. In the present study, an axisymmetric minimum length nozzle was firstly designed using method of characteristics. Then, streamlines trace technique with an offset circular entrance was adopted to extract the three-dimensional asymmetric noz

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Sharapov, A. I., A. A. Chernykh, and A. V. Peshkova. "Supersonic flow of two-phase gas- droplet flows in nozzles." Power engineering: research, equipment, technology 21, no. 3 (2019): 86–98. http://dx.doi.org/10.30724/1998-9903-2019-21-3-86-96.

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For practical applications, the description of processes occurring during the flow of two-phase gas-liquid mixtures requires a simple physical and mathematical model that describes the behavior of a two-phase medium in the entire range of phase concentrations changes and in a wide range of pressure changes. Problems of this kind arise in various branches of industry and technology. In the space industry, one often has to deal with the movement of various gases in rocket nozzles, consider the combustion, condensation of various vapors on the nozzle walls and their further impact on the velocity

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Vinayaka Nagarajaiah, Sara Solomon Raj, Ayampalayam Nanjappan Swaminathen, Paluru Kiran Kumar, Chintala Indira Priyadarsini, and Kodipaka Mamatha. "Optimization of Process Parameters for Flow Nozzle with Different Geometry using Computational Fluid Dynamics Method." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 118, no. 1 (2024): 142–54. http://dx.doi.org/10.37934/arfmts.118.1.142154.

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A nozzle is a tubular structure designed to facilitate the flow of hot gases. Rocket nozzle designs typically consist of a stationary convergent section and a stationary divergent section. The term "CD" is an abbreviation for "convergent-divergent" and is used to refer to this specific nozzle type. Upgrades are being made to nozzles and other engine components in order to enhance performance and optimise thrust delivery. Application-specific improvements will be made to rocket nozzles and other current combustion expansion systems. An instance of such progress is the implementation of the bell

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Wu, Shenghao, Daxiong Liao, Jiming Chen, Qin Chen, and Haitao Pei. "Supersonic Nozzle Optimization Design with Spline Curves Fitting the Nozzle Profiles." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 36, no. 4 (2018): 785–91. http://dx.doi.org/10.1051/jnwpu/20183640785.

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Supersonic nozzle contour optimization design was applied to 0.6m×0.6m continuous transonic wind tunnel to improve flow quality in the test section. The Mach number root mean square deviation with the design value was chosen as optimization target. And the CFD results were verified with experimental results. Cubic spline curves with the optimal interpolating point distribution scheme were used to fit the nozzle contour. Efficient global optimization based on the Gaussian process surrogate model was used to reduce the times of evaluation. Results indicate that, the optimization framework can ge

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Xu, Dachuan, Yunsong Gu, Wei Li, and Jingxiang Chen. "Experimental Investigation of the Performance of a Novel Ejector–Diffuser System with Different Supersonic Nozzle Arrays." Fluids 9, no. 7 (2024): 155. http://dx.doi.org/10.3390/fluids9070155.

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The supersonic–supersonic ejector–diffuser system is employed to suck supersonic low-pressure and low-temperature flow into a high-pressure environment. A new design of a supersonic–supersonic ejector–diffuser was introduced to verify pressure control performance under different operating conditions and vacuum background pressure. A 1D analysis was used to predict the geometrical structure of an ejector–diffuser with a rectangular section based on the given operating conditions. Different numbers and types of nozzle plates were designed and installed on the ejector to study the realizability o

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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 (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

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Mendoza-Anchondo, Reyna Judith, Cornelio Alvarez-Herrera, and José Guadalupe Murillo-Ramírez. "Visualization and Parameters Determination of Supersonic Flows in Convergent-Divergent Micro-Nozzles Using Schlieren Z-Type Technique and Fluid Mechanics." Fluids 10, no. 2 (2025): 40. https://doi.org/10.3390/fluids10020040.

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Small-scale and supersonic convergent-divergent type micro-nozzles with characteristic sizes of around a few centimeters and exit and throat radii of tenths of millimeters were the subjects of this study. Using the schlieren Z-type optical technique, the supersonic airflows established at the exit of seven nozzles were visualized. The dependence of the shock cell characteristics on the nozzle pressure ratio (NPR), defined as the ratio of stagnation pressure to atmospheric pressure, was analyzed. The dependence of the nozzle thrust and the specific impulse on the NPR ratio and the mass flow rat

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WATANABE, Yasushi, Shigeru MATSUO, and Fumio HIGASHINO. "Visualization of Supersonic Nozzle Flows." Journal of the Visualization Society of Japan 12, no. 1Supplement (1992): 147–50. http://dx.doi.org/10.3154/jvs.12.1supplement_147.

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

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SHEN, Junmou, Jingang DONG, Ruiqu LI, et al. "Integrated supersonic wind tunnel nozzle." Chinese Journal of Aeronautics 32, no. 11 (2019): 2422–32. http://dx.doi.org/10.1016/j.cja.2019.07.005.

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Williamson, R. G., S. H. Moustapha, and J. P. Huot. "The Effect of a Downstream Rotor on the Measured Performance of a Transonic Turbine Nozzle." Journal of Turbomachinery 108, no. 2 (1986): 269–74. http://dx.doi.org/10.1115/1.3262047.

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Two nozzle designs, involving the same low aspect ratio, high turning angle vanes, and differing in outer wall contour, were tested over a range of exit Mach numbers up to supersonic values. The experiments were conducted on a large-scale, full annular configuration with and without a representative rotor downstream. Nozzle performance was found to be significantly affected by rotor operation, the influence depending on the detailed characteristics of the nozzle flow field, as well as on the design and operation of the rotor itself. It is suggested that performance evaluation of low aspect rat

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