Log in

Relevant bibliographies by topics / Aerospike Nozzle / Journal articles

To see the other types of publications on this topic, follow the link: Aerospike Nozzle.

Journal articles on the topic 'Aerospike Nozzle'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 50 journal articles for your research on the topic 'Aerospike Nozzle.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse journal articles on a wide variety of disciplines and organise your bibliography correctly.

1

Lai, A., S. S. Wei, C. H. Lai, et al. "Comparison of the Propulsion Performance of Aerospike and Bell-Shaped Nozzle Using Hydrogen Peroxide Monopropellant Under Sea-Level Condition." Journal of Mechanics 35, no. 3 (2018): 427–40. http://dx.doi.org/10.1017/jmech.2018.18.

Full text

Abstract:

ABSTRACTThis study investigates numerically the performance of applying aerospike nozzle in a hydrogen peroxide mono-propellant propulsion system. A set of governing equations, including continuity, momentum, energy and species conservation equations with extended k-ε turbulence equations, are solved using the finite-volume method. The hydrogen peroxide mono-propellant is assumed to be fully decomposed into water vapor and oxygen after flowing through a catalyst bed before entering the nozzle. The aerospike nozzle is expected to have high performance even in deep throttling cases due to its se

APA, Harvard, Vancouver, ISO, and other styles

2

Menon, Pranav. "Investigation of Variation in the Performance of an Electro Thermal Thruster with Aerospike Nozzle." Advanced Engineering Forum 16 (April 2016): 91–103. http://dx.doi.org/10.4028/www.scientific.net/aef.16.91.

Full text

Abstract:

One of the most recently developed modes of propulsion is electric propulsion. The commonly used chemical propulsion systems have the advantage of a high Specific Impulse as compared to that of ion propulsion systems. However, owing to the efficacy of ion propulsion systems, it is considered the future of space exploration.Electro thermal thrusters produce thrust by using electrical fields to force hot plasma out of the nozzle with certain exit velocity. The plasma’s exit velocity and the system’s thrust capacity, as of now, are insufficient for space travel to be conducted within a reasonable

APA, Harvard, Vancouver, ISO, and other styles

3

Korte, J. J., A. O. Salas, H. J. Dunn, et al. "Multidisciplinary Approach to Linear Aerospike Nozzle Design." Journal of Propulsion and Power 17, no. 1 (2001): 93–98. http://dx.doi.org/10.2514/2.5712.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Bogoi, Alina, Radu D. Rugescu, Valentin Ionut Misirliu, Florin Radu Bacaran, and Mihai Predoiu. "Inviscid Nozzle for Aerospike Rocket Engine Application." Applied Mechanics and Materials 811 (November 2015): 152–56. http://dx.doi.org/10.4028/www.scientific.net/amm.811.152.

Full text

Abstract:

A computational method for the steady 2-D flow in axially symmetrical rocket nozzles with a given profile is developed, in order to determine the Maximum thrust contour of rocket engine nozzles with large expansion ratio. The optimized nozzles proved a more than 10% increase in the integral specific impulse recorded during the variable altitude atmospheric flight of rocket vehicles. The method is well suited for application in the design of the optimum contour for axially-symmetric nozzles for atmospheric rocket ascent, specifically for aerospike type nozzles, as for other similar industrial a

APA, Harvard, Vancouver, ISO, and other styles

5

., Vinay Kumar Levaka. "DESIGN AND FLOW SIMULATION OF TRUNCATED AEROSPIKE NOZZLE." International Journal of Research in Engineering and Technology 03, no. 11 (2014): 122–31. http://dx.doi.org/10.15623/ijret.2014.0311019.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Naveen Kumar, K., M. Gopalsamy, Daniel Antony, R. Krishnaraj, and Chaparala B. V. Viswanadh. "Design and Optimization of Aerospike nozzle using CFD." IOP Conference Series: Materials Science and Engineering 247 (October 2017): 012008. http://dx.doi.org/10.1088/1757-899x/247/1/012008.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Wang, Chang-Hui, Yu Liu, and Li-Zi Qin. "Aerospike nozzle contour design and its performance validation." Acta Astronautica 64, no. 11-12 (2009): 1264–75. http://dx.doi.org/10.1016/j.actaastro.2008.01.045.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Chaudhari, Krunal C. "Analysis of Aerospike Nozzle Structural Contour Design Performance Optimization." International Journal for Research in Applied Science and Engineering Technology V, no. X (2017): 1000–1004. http://dx.doi.org/10.22214/ijraset.2017.10144.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Sankari Ashok Alshiya, K., M. Santhosh, V. K. Santhosh, and S. Sai Gopal. "Experimental analysis of jet flow in an aerospike nozzle." Materials Today: Proceedings 46 (2021): 3444–50. http://dx.doi.org/10.1016/j.matpr.2020.11.783.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Ferlauto, Michele, Andrea Ferrero, Matteo Marsicovetere, and Roberto Marsilio. "Differential Throttling and Fluidic Thrust Vectoring in a Linear Aerospike." International Journal of Turbomachinery, Propulsion and Power 6, no. 2 (2021): 8. http://dx.doi.org/10.3390/ijtpp6020008.

Full text

Abstract:

Aerospike nozzles represent an interesting solution for Single-Stage-To-Orbit or clustered launchers owing to their self-adapting capability, which can lead to better performance compared to classical nozzles. Furthermore, they can provide thrust vectoring in several ways. A simple solution consists of applying differential throttling when multiple combustion chambers are used. An alternative solution is represented by fluidic thrust vectoring, which requires the injection of a secondary flow from a slot. In this work, the flow field in a linear aerospike nozzle was investigated numerically an

APA, Harvard, Vancouver, ISO, and other styles

11

Takahashi, Hidemi. "Practical Approach for Absolute Density Field Measurement Using Background-Oriented Schlieren." Aerospace 5, no. 4 (2018): 129. http://dx.doi.org/10.3390/aerospace5040129.

Full text

Abstract:

A practical approach for deriving the absolute density field based on the background-oriented schlieren method in a high-speed flowfield was implemented. The flowfield of interest was a two-dimensional compressible flowfield created by two supersonic streams to simulate a linear aerospike nozzle operated under a supersonic in-flight condition. The linear aerospike nozzle had a two-dimensional cell nozzle with a design Mach number of 3.5, followed by a spike nozzle. The external flow simulating the in-flight condition was 2.0. The wall density distribution used as the wall boundary condition fo

APA, Harvard, Vancouver, ISO, and other styles

12

Eilers, Shannon D., Matthew D. Wilson, Stephen A. Whitmore, and Zachary W. Peterson. "Side-Force Amplification on an Aerodynamically Thrust-Vectored Aerospike Nozzle." Journal of Propulsion and Power 28, no. 4 (2012): 811–19. http://dx.doi.org/10.2514/1.b34381.

Full text

APA, Harvard, Vancouver, ISO, and other styles

13

Udaiyakumar, K. C., Kartik Venkataramani Iyer, V. Akhil, Anshul Motwani, and Vibhor Rajesh Bhaise. "Numerical Simulation and Contour Design of Aerospike Nozzle: a Behavioural Study on Truncation Effects of Nozzle." International Review of Aerospace Engineering (IREASE) 13, no. 4 (2020): 141. http://dx.doi.org/10.15866/irease.v13i4.17343.

Full text

APA, Harvard, Vancouver, ISO, and other styles

14

Simmons, J., and Richard Branam. "Parametric Study of Dual-Expander Aerospike Nozzle Upper-Stage Rocket Engine." Journal of Spacecraft and Rockets 48, no. 2 (2011): 355–67. http://dx.doi.org/10.2514/1.51534.

Full text

APA, Harvard, Vancouver, ISO, and other styles

15

Verma, S. B. "Performance Characteristics of an Annular Conical Aerospike Nozzle with Freestream Effect." Journal of Propulsion and Power 25, no. 3 (2009): 783–91. http://dx.doi.org/10.2514/1.40302.

Full text

APA, Harvard, Vancouver, ISO, and other styles

16

Balaji, G., B. Navin Kumar, J. Vijayarangam, A. Vasudevan, and R. Pandiyarajan. "Numerical investigation of expansion Fan optimization of truncated annular aerospike nozzle." Materials Today: Proceedings 46 (2021): 4283–88. http://dx.doi.org/10.1016/j.matpr.2021.03.124.

Full text

APA, Harvard, Vancouver, ISO, and other styles

17

SHIBAO, Masafumi, Nobuyuki TSUBOI, and Takashi ITO. "808 Numerical Analysis of the Aerospike Nozzle for the Evaluation of Performance : Effect of Inner Nozzle Configuration." Proceedings of Conference of Kyushu Branch 2014.67 (2014): _808–1_—_808–2_. http://dx.doi.org/10.1299/jsmekyushu.2014.67._808-1_.

Full text

APA, Harvard, Vancouver, ISO, and other styles

18

MORI, Hideo, Hiroki YAMAGUCHI, Atsushi FUKUSHIMA, Masateru FUTAMURA, and Tomohide NIIMI. "Sidewall Shape Optimization for Linear Aerospike Nozzle using NO-LIF and PSP." Journal of the Visualization Society of Japan 27, Supplement2 (2007): 185–86. http://dx.doi.org/10.3154/jvs.27.supplement2_185.

Full text

APA, Harvard, Vancouver, ISO, and other styles

19

Rajesh, G., Gyanesh Kumar, H. D. Kim, and Mathew George. "Computational and Experimental Simulations of the Flow Characteristics of an Aerospike Nozzle." Journal of the Korean Society of Visualization 10, no. 1 (2012): 47–54. http://dx.doi.org/10.5407/jksv.2011.10.1.047.

Full text

APA, Harvard, Vancouver, ISO, and other styles

20

Tian, Hui, Zihao Guo, Zhu Hao, Liu Hedong, and Chengen Li. "Numerical and experimental investigation of throttleable hybrid rocket motor with aerospike nozzle." Aerospace Science and Technology 106 (November 2020): 105983. http://dx.doi.org/10.1016/j.ast.2020.105983.

Full text

APA, Harvard, Vancouver, ISO, and other styles

21

Noori, S., and A. Shahrokhi. "The Influence of Different Turbulence Models on the FlowField Characteristics of an Aerospike Nozzle." Applied Mechanics and Materials 110-116 (October 2011): 437–43. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.437.

Full text

Abstract:

To improve the calculation of the flow properties of an aerospike nozzle, different turbulent models are studied in this research. The primary shape of the nozzle and the plug is determined through utilizing an approximate method. The flow field is then simulated using Navier-Stokes equations for compressible flow. The computational methodology utilizes steady state density-based formulation and a finite volume cell centered scheme to discretize the flow field equations. To accelerate the solution convergence, the flow field is divided into several zones. Each zone is facilitated with proper u

APA, Harvard, Vancouver, ISO, and other styles

22

TANIGUCHI, Mashio, Hideo MORI, Ryutaro NISHIHIRA, Atsushi FUKUSHIMA, and Tomohide NIIMI. "Investigation of Linear-Type Aerospike Nozzle with Sidewalls using NO-LIF and PSP." Journal of the Visualization Society of Japan 25, Supplement1 (2005): 335–38. http://dx.doi.org/10.3154/jvs.25.supplement1_335.

Full text

APA, Harvard, Vancouver, ISO, and other styles

23

Niimi, Tomohide, Hideo Mori, Kazuki Okabe, Yusuke Masai, and Mashio Taniguchi. "Visualization and Analyses of Jet Structures from a Cluster-Type Linear Aerospike Nozzle." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 52, no. 605 (2004): 235–40. http://dx.doi.org/10.2322/jjsass.52.235.

Full text

APA, Harvard, Vancouver, ISO, and other styles

24

Karthikeyan, T., S. K. Aravindhkumar, and J. Arun Kumar. "Design and Analysis of Aerospike Nozzle to Improve Thrust in Hybrid Rocket Engine." International Journal of Engineering Trends and Technology 36, no. 7 (2016): 347–51. http://dx.doi.org/10.14445/22315381/ijett-v36p265.

Full text

APA, Harvard, Vancouver, ISO, and other styles

25

Swathi, Gorle, Chaganti Satya Sandeep, Mandapudi Snigdha, Gudikandula Sravanthi, and Dussa Govardhan. "Three Dimensional Computational Flow Simulation of Truncated Aerospike Nozzle Considering Different Plug Lengths." Indian Journal of Science and Technology 10, no. 13 (2017): 1–4. http://dx.doi.org/10.17485/ijst/2017/v10i13/111909.

Full text

APA, Harvard, Vancouver, ISO, and other styles

26

Cheah, Kean How, and Jit Kai Chin. "DESIGN AND FABRICATION OF MICRONOZZLES." IIUM Engineering Journal 12, no. 1 (2011): 51–62. http://dx.doi.org/10.31436/iiumej.v12i1.65.

Full text

Abstract:

Micronozzle, a key component in micropropulsion system, has been designed and fabricated. Quasi 1D inviscid theory was used in designing a series of conical micronozzles of different expander half-angles (10Â°-50Â°). Aerospike micronozzle, a promising candidate to achieve high performance propulsion system, was designed with Angelino method (or Approximate method). Both micronozzles were fabricated using soft lithography, an inexpensive and relatively simple technique comparing to well-established deep reactive ion etching (DRIE) technique, with polydimethylsiloxane (PDMS) as structural materi

APA, Harvard, Vancouver, ISO, and other styles

27

NARIMIYA, Tadashi, Nobuyuki TSUBOI, and Takashi ITO. "811 Numerical analysis of the aerospike nozzle flow fields for the evaluation of performance." Proceedings of Conference of Kyushu Branch 2012.65 (2012): 287–88. http://dx.doi.org/10.1299/jsmekyushu.2012.65.287.

Full text

APA, Harvard, Vancouver, ISO, and other styles

28

Ito, Takashi, and Kozo Fujii. "Flow Field and Performance Analysis of an Annular-Type Aerospike Nozzle with Base Bleeding." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 46, no. 151 (2003): 17–23. http://dx.doi.org/10.2322/tjsass.46.17.

Full text

APA, Harvard, Vancouver, ISO, and other styles

29

He, Miaosheng, Lizi Qin, and Yu Liu. "Numerical investigation of flow separation behavior in an over-expanded annular conical aerospike nozzle." Chinese Journal of Aeronautics 28, no. 4 (2015): 983–1002. http://dx.doi.org/10.1016/j.cja.2015.06.016.

Full text

APA, Harvard, Vancouver, ISO, and other styles

30

NIIMI, Tomohide, Hideo MORI, Mashio TANIGUCHI, and Ryutaro NISHIHIRA. "Experimental Analyses of Jet Structures around Clustered Linear Aerospike Nozzle by NO-LIF and PSP." Journal of the Visualization Society of Japan 24, Supplement1 (2004): 155–56. http://dx.doi.org/10.3154/jvs.24.supplement1_155.

Full text

APA, Harvard, Vancouver, ISO, and other styles

31

TANIGUCHI, Mashio, Hideo MORI, Ryutaro NISHIHIRA, and Tomohide NIIMI. "Experimental Analyses of Jet Structures around Clustered Linear Aerospike Nozzle by NO-LIF and PSP." Transaction of the Visualization Society of Japan 26, no. 2 (2006): 13–18. http://dx.doi.org/10.3154/tvsj.26.13.

Full text

APA, Harvard, Vancouver, ISO, and other styles

32

TANIGUCHI, Mashio, Hideo MORI, Ryutaro NISHIHIRA, and Tomohide NIIMI. "Experimental Investigation of Sidewall-Effect on Linear-Type Aerospike Nozzle using NO-LIF and PSP." Transaction of the Visualization Society of Japan 26, no. 10 (2006): 97–104. http://dx.doi.org/10.3154/tvsj.26.97.

Full text

APA, Harvard, Vancouver, ISO, and other styles

33

Jourdaine, Nicolas, Nobuyuki Tsuboi, Kohei Ozawa, Takayuki Kojima, and A. Koichi Hayashi. "Three-dimensional numerical thrust performance analysis of hydrogen fuel mixture rotating detonation engine with aerospike nozzle." Proceedings of the Combustion Institute 37, no. 3 (2019): 3443–51. http://dx.doi.org/10.1016/j.proci.2018.09.024.

Full text

APA, Harvard, Vancouver, ISO, and other styles

34

TANIGUCHI, Mashio, Hideo MORI, Ryutaro NISHIHIRA, and Tomohide NIIMI. "Experimental Analyses of Flow Field around Linear-Type Aerospike Nozzle with Sidewall by NO-LIF and PSP." Proceedings of the Fluids engineering conference 2004 (2004): 311. http://dx.doi.org/10.1299/jsmefed.2004.311.

Full text

APA, Harvard, Vancouver, ISO, and other styles

35

Huang, Yue, Hanqing Xia, Xiaonan Chen, Zhenye Luan, and Yancheng You. "Shock dynamics and expansion characteristics of an aerospike nozzle and its interaction with the rotating detonation combustor." Aerospace Science and Technology 117 (October 2021): 106969. http://dx.doi.org/10.1016/j.ast.2021.106969.

Full text

APA, Harvard, Vancouver, ISO, and other styles

36

Ashley, Steven. "Bringing Launch Costs Down to Earth." Mechanical Engineering 120, no. 10 (1998): 62–68. http://dx.doi.org/10.1115/1.1998-oct-1.

Full text

Abstract:

This article discusses the three federally funded projects that are underway to develop new rocket engines that can make it more affordable to send payloads into orbits. The new RS-68 propulsion system is Rocketdyne's entry in competition to power the US Air Force's new heavy-lift booster. The most ambitious of the new propulsion system designs is Rocketdyne's XRS-2200 linear aerospike engine, a seemingly nozzle-less oxygen/hydrogen powerplant that is designed to send the autonomously controlled NASA X-33 lifting body into orbit. The X-33 is being developed by Lockheed Martin Skunk Works, Palm

APA, Harvard, Vancouver, ISO, and other styles

37

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.

Full text

Abstract:

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

APA, Harvard, Vancouver, ISO, and other styles

38

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.

Full text

Abstract:

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

APA, Harvard, Vancouver, ISO, and other styles

39

V. Paul, Roy, Kriparaj K.G., and Tide P.S. "Numerical predictions of the flow characteristics of subsonic jet emanating from corrugated lobed nozzle." Aircraft Engineering and Aerospace Technology 92, no. 7 (2020): 955–72. http://dx.doi.org/10.1108/aeat-03-2019-0041.

Full text

Abstract:

Purpose The purpose of this study is to investigate the aerodynamic characteristics of subsonic jet emanating from corrugated lobed nozzle. Design/methodology/approach Numerical simulations of subsonic turbulent jets from corrugated lobed nozzles using shear stress transport k-ω turbulence model have been carried out. The analysis was carried out by varying parameters such as lobe length, lobe penetration and lobe count at a Mach number of 0.75. The numerical predictions of axial and radial variation of the mean axial velocity, u′u′ ¯ and v′v′ ¯ have been compared with experimental results of

APA, Harvard, Vancouver, ISO, and other styles

40

Elangovan, S., and E. Rathakrishnan. "Studies on high speed jets from nozzles with internal grooves." Aeronautical Journal 108, no. 1079 (2004): 43–50. http://dx.doi.org/10.1017/s000192400000498x.

Full text

Abstract:

Experiments were carried out on jets issuing from circular nozzles with grooved exits and the results compared with those of the plain nozzle. The plain nozzle had an exit diameter of 10mm. Because of the introduction of semi-circular grooves at the exit, the effective or equivalent diameter of the grooved nozzles was 10·44mm. The groove lengths were varied as 3, 5 and 8mm. The nozzles were operated at fully expanded sonic and underexpanded exit conditions. The corresponding fully expanded Mach numbers were 1·0 and 1·41. The shock cell structure of the underexpanded jets from grooved nozzles a

APA, Harvard, Vancouver, ISO, and other styles

41

Dong, Pengbo, Keiya Nishida, and Youichi Ogata. "Characterization of multi-hole nozzle sprays and internal flow for different nozzle hole lengths in direct-injection diesel engines." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 231, no. 4 (2016): 500–515. http://dx.doi.org/10.1177/0954407016653890.

Full text

Abstract:

Multi-hole nozzles have a wide range of application in the fuel supply system of modern diesel engines, although single-hole nozzles dominate basic internal flow and spray research. The parameters of the nozzle geometry are crucial factors that can alter the internal flow dynamics of the nozzle and the consequent spray behaviours. The novelty of this study lies in implementing the application of practical prototype mini-sac multi-hole diesel nozzles to experimental and numerical studies. The internal flow and spray characteristics generated by practical multi-hole (10-hole) nozzles with differ

APA, Harvard, Vancouver, ISO, and other styles

42

Shan, Yong, Xiaoming Zhou, Xiaoming Tan, Jingzhou Zhang, and Yanhua Wu. "Parametric Design Method and Performance Analysis of Double S-Shaped Nozzles." International Journal of Aerospace Engineering 2019 (May 12, 2019): 1–24. http://dx.doi.org/10.1155/2019/4694837.

Full text

Abstract:

A parametric design method, which was based on super-elliptical transition and self-adaption infrared radiation shield for the double S-shaped nozzle, was introduced. The complete shielding of high-temperature components in the S-shaped nozzle was realized. Model experiments and numerical simulations were performed to investigate the effects of offset ratio S/D, the ratio of length to diameter L/D, and the aspect ratio W/H on the aerodynamics and infrared radiation. The results showed that the total pressure recovery and thrust coefficients were improved initially, but dropped rapidly with the

APA, Harvard, Vancouver, ISO, and other styles

43

Salvador, Francisco J., Joaquin de la Morena, Marcos Carreres, and David Jaramillo. "Numerical analysis of flow characteristics in diesel injector nozzles with convergent-divergent orifices." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 231, no. 14 (2017): 1935–44. http://dx.doi.org/10.1177/0954407017692220.

Full text

Abstract:

The geometry of diesel injector nozzles is known to significantly affect the characteristic spray behavior and emissions formation. In this paper, a novel nozzle concept, consisting of orifices with a convergent–divergent shape, is investigated through Computational Fluid Dynamics techniques. Three of these nozzles, characterized by different degrees of conicity, are compared to a nozzle with cylindrical orifices, which acts as a baseline. A homogeneous equilibrium model, validated against experimental data in previous works by the authors, is used to calculate the eventual cavitation formatio

APA, Harvard, Vancouver, ISO, and other styles

44

Schuckert, Sebastian, Oliver Hofmann, and Georg Wachtmeister. "Experimental investigation into simulated aging effects of common-rail injector nozzles: Influences on injection rate, spray characteristics, and engine performance." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 234, no. 2-3 (2019): 349–62. http://dx.doi.org/10.1177/0954407019855289.

Full text

Abstract:

Emission performance of combustion engines has gained outstanding importance with both legislators and customers over the past years. Injector aging, such as nozzle wear or coking, results in the deterioration of injection and emission parameters. In this study, the influences of aging effects on injection rate, fuel spray as well as engine performance and emissions were assessed. Nozzles, which had previously been operated in a vehicle engine and were likely to have suffered from aging, showed no aging-induced characteristics during injection rate and spray measurements and were not investiga

APA, Harvard, Vancouver, ISO, and other styles

45

B.T., Kannan, and Panchapakesan N.R. "Effect of momentum flux distribution on multiple round jets." Aircraft Engineering and Aerospace Technology 90, no. 2 (2018): 452–60. http://dx.doi.org/10.1108/aeat-11-2016-0233.

Full text

Abstract:

Purpose This study aims to investigate the effects of nozzle momentum flux distribution on the flow field characteristics. Design/methodology/approach The nozzle configuration consists of a central nozzle surrounded by four nozzles. All nozzles have the same diameter and constant separation between nozzles. OpenFOAM® is used for simulating the jet flow. Reynolds-averaged Navier-Stokes (RANS) equations are solved iteratively with a first-order closure for turbulence. Pitot-static tube with differential pressure transducer is used for mean velocity measurements. The comparison of computed result

APA, Harvard, Vancouver, ISO, and other styles

46

Dix, J., A. J. Saddington, K. Knowles, and M. A. Richardson. "Infra-red signature reduction study on a small-scale jet engine." Aeronautical Journal 109, no. 1092 (2005): 83–88. http://dx.doi.org/10.1017/s0001924000000580.

Full text

Abstract:

Abstract This paper presents infra-red signature data for a small-scale, low pressure ratio turbojet engine typical of that used in unmanned air vehicle applications. The aim of the study was to test a number of different convergent nozzle designs concentrating on those with trailing edge modifications. The engine used in the tests has a single stage centrifugal compressor and radial inflow turbine and is designed to produce approximately 150N of thrust at 103,500rpm using liquid propane fuel. The test rig consisted of a calibrated thrust stand whilst the engine was controlled through an elect

APA, Harvard, Vancouver, ISO, and other styles

47

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.

Full text

Abstract:

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

APA, Harvard, Vancouver, ISO, and other styles

48

Bermúdez, V., R. Payri, F. J. Salvador, and A. H. Plazas. "Study of the influence of nozzle seat type on injection rate and spray behaviour." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 219, no. 5 (2005): 677–89. http://dx.doi.org/10.1243/095440705x28303.

Full text

Abstract:

A deep analysis of the injection rate characteristics and spray behaviour of the most used nozzle types in diesel engines [microSAC and valve covered orifice (VCO)] has been carried out. In order to compare the injection characteristics and the spray behaviour of both nozzle types, several experimental installations were used, such as the steady flow test rig, injection rate test rig, spray momentum test rig, and nitrogen test rig, to obtain a full hydrodynamic and spray characterization. The study of the flow in both nozzles was analysed under steady flow conditions in the steady flow test ri

APA, Harvard, Vancouver, ISO, and other styles

49

Laitón, Sergio Nicolas Pachón, João Felipe de Araujo Martos, Israel da Silveira Rego, George Santos Marinho, and Paulo Gilberto de Paula Toro. "Experimental Study of Single Expansion Ramp Nozzle Performance Using Pitot Pressure and Static Pressure Measurements." International Journal of Aerospace Engineering 2019 (February 27, 2019): 1–11. http://dx.doi.org/10.1155/2019/7478129.

Full text

Abstract:

In order to overcome the drag at hypersonic speed, hypersonic flight vehicles require a high level of integration between the airframe and the propulsion system. Propulsion system based on scramjet engine needs a close interaction between its aerodynamics and stability. Hypersonic vehicle nozzles which are responsible for generating most of the thrust generally are fused with the vehicle afterbody influencing the thrust efficiency and vehicle stability. Single expansion ramp nozzles (SERN) produce enough thrust necessary to hypersonic flight and are the subject of analysis of this work. Flow e

APA, Harvard, Vancouver, ISO, and other styles

50

Li, Shangze, Yufei Zhang, Haixin Chen, and Kaiwen Deng. "Aerodynamic Optimization of Turbine Based Combined Cycle Nozzle." International Journal of Turbo & Jet-Engines 35, no. 4 (2018): 385–94. http://dx.doi.org/10.1515/tjj-2016-0052.

Full text

Abstract:

Abstract This paper aims at optimizing a Turbine Based Combined Cycle (TBCC) nozzle for upgrading its aerodynamic performance in multiple flight conditions. An in-house RANS solver called NSAWET is employed for aerodynamic evaluation. The optimizer is a differential evolution algorithm combined with a response surface. Firstly, a two-dimensional model of the initial TBCC nozzle system is investigated. The flow field of the nozzle contains complicated shockwave interactions that cause thrust loss. Then multi-point aerodynamic optimization of a two-dimensional ramjet nozzle is carried out, which

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!