The interaction of a Prandtl–Meyer wave and a quasi-one-dimensional flow region

Silnikov, М.V.; Чернышов, М. В.

doi:10.1016/j.actaastro.2014.11.010

Cited by 19 publications

(15 citation statements)

References 9 publications

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“…и с учетом (1) и других известных соотношений для скачков уплотнения -производные его интенсивности (dJ/dw) и других параметров течения (статического давления, энтропии, числа Маха) за скачком по направлению его падения, если известны параметры течения перед ним (в устье струи). Дифференциальные условия динамической совместности успешно использовались ранее при анализе характеристик поля течения Прандтля-Майера [24], взаимодействия этих волн с догоняющими [20] и встречными [22] скачками уплотнения, а также позволили провести анализ плоского струйного истечения в окрестности кромки сопла [23] при условии задания всех характеристик потока перед сходящим с кромки скачком.…”

Section: схема течения основные соотношенияunclassified

“…Широко известная [24][25][26] модель течения по расширяющемуся соплу с коническими образующими или по соплу с равномерным потоком в выходном сечении (модель сверхзвукового истечения из цилиндрического или сферического источника) предполагает следующие соотношения для основных неравномерностей перед скачком в точке A [21,24]:…”

Section: схема течения основные соотношенияunclassified

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Дифференциальные Характеристики Поля Течения Перерасширенной Газовой Струи В Окрестности Кромки Сопла

Чернышов¹,

Гвоздева²

2019

Журнал Технической Физики

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A parametric study of the features of the flow field of a plane and axisymmetric overexpanded ideal gas jet in the vicinity of the nozzle edge has been conducted over the entire theoretically admissible range of determining parameters (nozzle divergence angles, exhaust Mach numbers, jet incalculabilities, and gas adiabat indicators). The exhaust parameters that correspond to the extremes of the differential characteristics of a shockwave falling (descending) from the edge and the flow field behind it have been revealed. A significant difference in the character of changes in the characteristics of the shockwave and the flow field behind it depending on the type of symmetry of the gas jet has been found and studied.

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Section: схема течения основные соотношенияunclassified

Дифференциальные Характеристики Поля Течения Перерасширенной Газовой Струи В Окрестности Кромки Сопла

Чернышов¹,

Гвоздева²

2019

Журнал Технической Физики

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“…The Sod problem constitutes a particularly interesting and difficult test case, since it presents an exact solution to the full system of 1D Euler equations containing simultaneously a shock wave, a contact discontinuity, and an expansion fan [33]. The analogous 2D steady expansion wave and its interaction is discussed in [34,35]. This problem is chosen to validate the numerical schemes and assess the temporal accuracy The time required for calculation of one time step, and speedup of calculations are given in the Table 1 (time is given in milliseconds).…”

Section: Sod Problemmentioning

confidence: 99%

Analysis of impact of general-purpose graphics processor units in supersonic flow modeling

et al. 2017

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Computational methods are widely used in prediction of complex flowfields associated with off-normal situations in aerospace engineering. Modern graphics processing units (GPU) provide architectures and new programming models that enable to harness their large processing power and to design computational fluid dynamics (CFD) simulations at both high performance and low cost. Possibilities of the use of GPUs for the simulation of external and internal flows on unstructured meshes are discussed. The finite volume method is applied to solve three-dimensional unsteady compressible Euler and Navier-Stokes equations on unstructured meshes with high resolution numerical schemes. CUDA technology is used for programming implementation of parallel computational algorithms. Solutions of some benchmark test cases on GPUs are reported, and the results computed are compared with experimental and computational data. Approaches to optimization of the CFD code related to the use of different types of memory are considered. Speedup of solution on GPUs with respect to the solution on central processor unit (CPU) is compared. Performance measurements show that numerical schemes developed achieve 20 to 50 speedup on GPU hardware compared to CPU reference implementation. The results obtained provide promising perspective for designing a GPU-based software framework for applications in CFD.

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“…The air flow rate is 20 kg/(m s) that corresponds to the propellant burning rate of 10 mm/s and density 9 of 2296 kg/m 3 . The Mach numbers based on the surface injection velocity is about 0.002.…”

Section: Figure 2 Geometry Of Channelmentioning

confidence: 99%

“…SRMs are subject to pressure oscillations caused by vortex shedding and acoustic feedback resulting from impingement of the vortices on the nozzle and other obstacles [3][4][5][6][7][8][9]. The oscillatory flowfield in a SRM consists of three distinct types of wave motions: acoustic (irrotational and compressible), vortical (rotational and incompressible) and entropy (arising from unsteady heat release) modes [10].…”

Section: Introductionmentioning

confidence: 99%

Pressure oscillations and instability of working processes in the combustion chambers of solid rocket motors

et al. 2017

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Cite this article as: V.N. Emelyanov, I.V. Teterina, K.N. Volkov and A.U. Garkushev, Pressure oscillations and instability of working processesin the combustion chambers of solid rocket motors, Acta Astronautica, http://dx.doi.org/10. 1016/j.actaastro.2016.09.029 This is a PDF file of an unedited manuscript that has been accepted for publication. As a service to our customers we are providing this early version of the manuscript. The manuscript will undergo copyediting, typesetting, and review of the resulting galley proof before it is published in its final citable form. Please note that during the production process errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain. AbstractMetal particles are widely used in space engineering to increase specific impulse and to supress acoustic instability of intra-champber processes. A numerical analysis of the internal injection-driven turbulent gas-particle flows is performed to improve the current understanding and modeling capabilities of the complex flow characteristics in the combustion chambers of solid rocket motors (SRMs) in presence of forced pressure oscillations. The two-phase flow is simulated with a combined Eulerian-Lagrangian approach. The Reynolds-averaged Navier-Stokes equations and transport equations of -model are solved numerically for the gas. The particulate phase is simulated through a Lagrangian deterministic and stochastic tracking models to provide particle trajectories and particle concentration. The results obtained highlight the crucial significance of the particle dispersion in turbulent flowfield and high potential of statistical methods. Strong coupling between acoustic oscillations, vortical motion, turbulent fluctuations and particle dynamics is observed.

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The interaction of a Prandtl–Meyer wave and a quasi-one-dimensional flow region

Cited by 19 publications

References 9 publications

Дифференциальные Характеристики Поля Течения Перерасширенной Газовой Струи В Окрестности Кромки Сопла

Дифференциальные Характеристики Поля Течения Перерасширенной Газовой Струи В Окрестности Кромки Сопла

Analysis of impact of general-purpose graphics processor units in supersonic flow modeling

Pressure oscillations and instability of working processes in the combustion chambers of solid rocket motors

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