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  • 1
    Online Resource
    Online Resource
    Blue Eyes Intelligence Engineering and Sciences Engineering and Sciences Publication - BEIESP ; 2019
    In:  International Journal of Engineering and Advanced Technology Vol. 9, No. 1s4 ( 2019-12-30), p. 1-4
    In: International Journal of Engineering and Advanced Technology, Blue Eyes Intelligence Engineering and Sciences Engineering and Sciences Publication - BEIESP, Vol. 9, No. 1s4 ( 2019-12-30), p. 1-4
    Abstract: Cavity performance in coaxial supersonic jets is investigated experimentally in a supersonic flow facility. The coaxial jets issued from the supersonic nozzle enter into a supersonic combustor in which the cavities are incorporated. The primary jet is maintained at a Mach of 1.32, while secondary jet is designed for Mach of 1.00, 1.11 and 1.45. The open type cavities are axisymmetric. The primary flow is maintained at a temperature of 1050K and the secondary flow is at atmospheric temperature. Static and stagnation pressures are measured by using a conventional pitot probe to analyze the quantitative mixing performance and total pressure loss. Uniform momentum flux distribution is observed in cavity configurations compared with nocavity. A more uniform mixing, as well as minimum stagnation pressure loss, is observed for cavity configuration - 4, L/D = 1.53, than other cavity configurations
    Type of Medium: Online Resource
    ISSN: 2249-8958
    Language: Unknown
    Publisher: Blue Eyes Intelligence Engineering and Sciences Engineering and Sciences Publication - BEIESP
    Publication Date: 2019
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  • 2
    Online Resource
    Online Resource
    SAGE Publications ; 2021
    In:  Proceedings of the Institution of Mechanical Engineers, Part M: Journal of Engineering for the Maritime Environment Vol. 235, No. 2 ( 2021-05), p. 600-606
    In: Proceedings of the Institution of Mechanical Engineers, Part M: Journal of Engineering for the Maritime Environment, SAGE Publications, Vol. 235, No. 2 ( 2021-05), p. 600-606
    Abstract: Flow noise originating in the turbulent boundary layer (TBL) often severely limits the performance of towed sonar array. Therefore, it is necessary to predict this noise for the design of an efficient towed array. This paper presents large eddy simulation methodology to establish the TBL properties and wall pressure fluctuations on a 12 m long towed array with length to diameter ratio of 1200 in the operating tow speed range of 2 to 5 knots in water. The computed flow noise levels are compared with experimental measurements available in the literature successfully. The effectiveness of scaling the flow noise spectra with the diameter and tow speed is discussed, and non-dimensional wall pressure spectra presented with respect to non-dimensional frequency. The overall sound pressure levels are also compared with experimental data that show good accuracy achieved by the proposed numerical methodology.
    Type of Medium: Online Resource
    ISSN: 1475-0902 , 2041-3084
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2021
    detail.hit.zdb_id: 2089895-2
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  • 3
    Online Resource
    Online Resource
    SAGE Publications ; 2021
    In:  Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science Vol. 235, No. 11 ( 2021-06), p. 1979-1991
    In: Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science, SAGE Publications, Vol. 235, No. 11 ( 2021-06), p. 1979-1991
    Abstract: Motivated by the requirement to lessen the aerodynamic drag and aeroacoustic sound of the bluff bodies, the present paper is devoted to a numerical analysis of the aerodynamics and aeroacoustics related with the flow past wavy circular cylinders. Based on the efficient flow control method, as has been presented by preceding researchers, the existing work embarks upon an investigation on the wavy cylinder at a various wavelength and amplitude conditions. Computations are performed for a circular cylinder of the length-to-diameter ratio ( L/ D) of 25 at a Reynolds number ( Re) of 97300 using large eddy simulation and Ffowcs Williams- Hawking’s acoustic analogy. Firstly, the cylinder without waviness is subjected to a uniform incoming flow is considered for validation against measurements. Secondly, various collection of wave shape parameters, specifically dimensionless wavelength λ/ D (=1 to 2.5), and wave amplitude a/ D (=0.05 to 0.2) have been taken into consideration. It is disclosed that the proper selection of shape parameters could significantly reduce the drag and sound emission levels, compared to the normal cylinder. Finally, a multi-objective particle swarm optimization was performed using the radial basis neural network to simultaneously reduce the aerodynamic drag and sound emission, with λ/ D and a/ D as design variables. We recognized a critical λ/ D and a/ D for the wavy circular cylinder at the considered subcritical Re.
    Type of Medium: Online Resource
    ISSN: 0954-4062 , 2041-2983
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2021
    detail.hit.zdb_id: 2024890-8
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  • 4
    Online Resource
    Online Resource
    Elsevier BV ; 2016
    In:  Procedia Computer Science Vol. 93 ( 2016), p. 975-981
    In: Procedia Computer Science, Elsevier BV, Vol. 93 ( 2016), p. 975-981
    Type of Medium: Online Resource
    ISSN: 1877-0509
    Language: English
    Publisher: Elsevier BV
    Publication Date: 2016
    detail.hit.zdb_id: 2557358-5
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  • 5
    Online Resource
    Online Resource
    Blue Eyes Intelligence Engineering and Sciences Engineering and Sciences Publication - BEIESP ; 2019
    In:  International Journal of Engineering and Advanced Technology Vol. 9, No. 1s4 ( 2019-12-30), p. 691-696
    In: International Journal of Engineering and Advanced Technology, Blue Eyes Intelligence Engineering and Sciences Engineering and Sciences Publication - BEIESP, Vol. 9, No. 1s4 ( 2019-12-30), p. 691-696
    Abstract: Experimental Investigations were carried out to study the performance of underwater launching missile system by adapting the electromagnetic launcher concept. There are two energy sources utilized to propel the missile in this proposed research; solid propellant motor and electromagnetic launcher. Electromagnetic launcher propels the missile from underwater to the water surface. Solid propellant motor propels the missile from water surface to the fixed target in the atmosphere. Solid propellants were prepared and the specific impulse of the propellants was also observed by impulse measuring system. 65/35 ratio of fuel-oxidizer (KNO3-Succrose) has the specific impulse of 89.3seconds. Rope test and vertical launch test were conducted for finding out the missile altitude and performance as well. The Electromagnetic launcher used in this research can replace torpedo tubes which are conventionally fitted with compressor supply. Since capacitor banks are being used as power source for the launcher, reusability and simplicity of the launching system are improved remarkably. The electromagnetic launcher generates Lorentz force to accelerate the missile through the water. 220VDC, 5000μFD capacitors connected in parallel produce 363N-m energy. 10grams of missile model made up of aluminium material was tested and found velocity and projectile of the missile.
    Type of Medium: Online Resource
    ISSN: 2249-8958
    Language: Unknown
    Publisher: Blue Eyes Intelligence Engineering and Sciences Engineering and Sciences Publication - BEIESP
    Publication Date: 2019
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  • 6
    Online Resource
    Online Resource
    IOP Publishing ; 2021
    In:  IOP Conference Series: Materials Science and Engineering Vol. 1128, No. 1 ( 2021-04-01), p. 012035-
    In: IOP Conference Series: Materials Science and Engineering, IOP Publishing, Vol. 1128, No. 1 ( 2021-04-01), p. 012035-
    Abstract: The dual combustion ramjet (DCR) engine is considered one of the promising engines for the hypersonic missile propulsion system. This paper reveals the non-reacting flow characteristics of the DCR engine with the influence of pylon and wall injections in coaxial jets using numerical investigation. The supersonic combustor of the DCR engine is modeled and analysed using the commercial CFD software ANSYS 18.0. The three-dimensional compressible Reynolds-averaged Navier-Stokes (RANS) equations coupled with the SST k - ω turbulence model have been used to analyse the coaxial mixing characteristics of the jets. The numerical study is validated with the experimental data and agrees with it for further investigation. The pylon and wall injectors are located symmetrically at the gas generator’s nozzle exit, and the air is used as the injectant to simulate gaseous fuel. The pylon and wall injection results are compared with the actual DCR engine. In a typical DCR engine, the shock waves generated from the gas generator nozzle enhance the mixing of the coaxial jets with minimum total pressure loss. The pylon injection induces more shock interactions along the flow direction within the supersonic combustor leading to higher total pressure loss than the wall injection. The pylon injection provides the spatial distribution of fuels compared to the wall injection in the coaxial supersonic flow field.
    Type of Medium: Online Resource
    ISSN: 1757-8981 , 1757-899X
    Language: Unknown
    Publisher: IOP Publishing
    Publication Date: 2021
    detail.hit.zdb_id: 2506501-4
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  • 7
    Online Resource
    Online Resource
    SAGE Publications ; 2022
    In:  International Journal of Engine Research Vol. 23, No. 9 ( 2022-09), p. 1495-1502
    In: International Journal of Engine Research, SAGE Publications, Vol. 23, No. 9 ( 2022-09), p. 1495-1502
    Abstract: The influence of pylon and wall injection in coaxial jets of a Dual Combustion Ramjet engine is numerically investigated in a non-reacting flow field. The supersonic combustor is modeled and analyzed using the commercial CFD software ANSYS 18.0. The three-dimensional compressible Reynolds-averaged Navier-Stokes (RANS) equations coupled with the SST k-ω turbulence model have been used to analyze the coaxial mixing characteristics of the jets. The numerical study is validated with the experimental data of the wall static pressures measured in the combustor’s flow direction. The pylon and wall injectors are located symmetrically at the gas generator’s exit nozzle, and the air is used as the injectant to simulate gaseous fuel. Three injection pressures are used for the study to understand the flow field characteristics in the injector regime. Also, the gas generator downstream direction is investigated. The shock waves generated from the gas generator nozzle enhance the mixing of the coaxial jets with minimum total pressure loss. The shock wave interactions are noticed with reducing intensity within the supersonic combustor for pylon injection, leading to higher total pressure loss than the wall injection. The pylon injection provides the spatial distribution of fuels compared to the wall injection in the coaxial supersonic flow field.
    Type of Medium: Online Resource
    ISSN: 1468-0874 , 2041-3149
    RVK:
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2022
    detail.hit.zdb_id: 2030603-9
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