Numerical simulation of the interaction of a transverse jet with a supersonic flow using different turbulence models

Волков, К. Н.; Emel’yanov, V. N.; Yakovchuk, M. S.

doi:10.1134/s0021894415050053

Cited by 14 publications

(10 citation statements)

References 28 publications

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“…Небольшое расхождение расчетных и экспериментальных данных в диапазоне −4 < x < −1, по всей видимости, обусловлено использованием k−ω модели турбулентности, которое, возможно, повлияло на область стыковки вдуваемой струи и основного потока вблизи стенки, что свидетельствует о том, что необходима дальнейшая модификация данной модели. Этот факт также подтверждает работа [14], которая посвящена струйному взаимодействию. В настоящей работе изучена применимость различных моделей турбулентности, а именно модели Спаларта−Альмараса, k−ε, k−ω и SST-моделей при решении подобных задач на основе сравнения вычислительных и экспериментальных данных.…”

Section: анализ результатовunclassified

“…Течения высокоскоростных струй в поперечном потоке обеспечивают эффективное смешивание топлива и окислителя, имеющего решающее значение для сверхзвукового горения. На данный момент известно большое количество экспериментальных [1][2][3][4][5] и теоретических [6][7][8][9][10][11][12][13][14] исследований, в которых достаточно хорошо изучен механизм образования ударно-волновой структуры струйного взаимодействия для умеренных параметров нерасчетности n (отношение давления в струе к давлению в потоке). Общую картину течения схематически можно представить следующим образом (рис.…”

Section: Introductionunclassified

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Detailed Comparative Analysis of Interaction of a Supersonic Flow with a Transverse Gas Jet at High Pressure Ratios

2019

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Section: анализ результатовunclassified

Section: Introductionunclassified

Detailed Comparative Analysis of Interaction of a Supersonic Flow with a Transverse Gas Jet at High Pressure Ratios

2019

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“…Calculations with the SST turbulence model were also carried out in [24] at high-flow temperatures. Various turbulence models were compared with the measured data in [25]. The injection of a stationary and pulsed jet from the surface of a flat plate into a supersonic flow was investigated in [26,27], and the injection of a jet into the supersonic part of the nozzle was studied in [28].…”

Section: Introductionmentioning

confidence: 99%

Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle

2021

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The optimal design of the thrust vector control system of solid rocket motors (SRMs) is discussed. The injection of a supersonic underexpanded gas jet into the diverging part of the rocket engine nozzle is considered, and multiparameter optimization of the geometric shape of the injection nozzle and the parameters of jet injection into a supersonic flow is developed. The turbulent flow of viscous compressible gas in the main nozzle and injection system is simulated with the Reynolds-averaged Navier–Stokes (RANS) equations and shear stress transport (SST) turbulence model. An optimization procedure with the automatic generation of a block-structured mesh and conjugate gradient method is applied to find the optimal parameters of the problem of interest. Optimization parameters include the pressure ratio of the injected jet, the angle of inclination of the injection nozzle to the axis of the main nozzle, the distance of the injection nozzle from the throat of the main nozzle and the shape of the outlet section of the injection nozzle. The location of injection nozzle varies from 0.1 to 0.9 with respect to the length of the supersonic part of the nozzle; the angle of injection varies from 30 to 160 degrees; and the shape of the outlet section of the injection nozzle is an ellipse with an aspect ratio that varies from 0.1 to 1. The computed fluid flow in the combustion chamber is compared with experimental and computational results. The dependence of the thrust as a function of the injection parameters is obtained, and conclusions are made about the effects of the input parameters of the problem on the thrust coefficient.

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“…SST turbulence model is implemented in the simulations, as it is proven to give excellent predictions compared to other turbulence models for the application of sonic jet injected in supersonic crossflow. 17,[42][43][44] The rhoCentralFoam solver with k À ! SST turbulence model has been validated with analytical results for an electrospray RF ion funnel 45 and with the experimental data for transonic turbulent flow over a deep cavity.…”

Section: Transport Propertiesmentioning

confidence: 99%

Modeling of a reaction control jet interacting with high-speed cross-flow in slip flow regime

Bhagat

Gijare

Dongari

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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Numerical investigation of a sonic reaction control jet interacting with the high-speed cross-flow has been carried out over a generic missile body. Simulations are performed in the early-hypersonic slip flow regime for air, CO2, and helium jet gases. An open source computational fluid dynamics tool, OpenFOAM is used to model the steady state, three-dimensional compressible Navier–Stokes equations with k-ω shear stress transport turbulence model. The conventional computational fluid dynamics solver is extended with additional features, such as transport of species, nonequilibrium boundary conditions for velocity slip and temperature jump, and a heat load calculation utility based on the sliding friction effect. The extended solver is validated with the direct simulation Monte Carlo results for the case of a sonic argon jet injected into hypersonic nitrogen cross-flow. The extended solver is able to accurately capture all the qualitative flow features like separation shock, bow shock, and barrel shock, and it also improves heat load predictions in the slip flow regime. The main objective of the present work is to study the effect of rarefaction and change in jet gas species on the complex flow topology, heat load distribution, and spread of jet gas on the missile body. Heat load predictions are found to be strongly dependent on the slip velocity of molecules in addition to the temperature gradient near the wall. The strength of a bow shock and a barrel shock is higher for helium jet, compared to air and CO2 jets, which spread more along the missile body, and weaker shocks and reduced heat load is generated. The current work is significant from the perspective of the thermal design of spacecraft surfaces and positioning of the optical sensors.

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Numerical simulation of the interaction of a transverse jet with a supersonic flow using different turbulence models

Cited by 14 publications

References 28 publications

Detailed Comparative Analysis of Interaction of a Supersonic Flow with a Transverse Gas Jet at High Pressure Ratios

Detailed Comparative Analysis of Interaction of a Supersonic Flow with a Transverse Gas Jet at High Pressure Ratios

Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle

Modeling of a reaction control jet interacting with high-speed cross-flow in slip flow regime

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