Shock wave bifurcation in channels with a bend

Kuzmin, Alexander

doi:10.1007/s00419-015-1062-z

Cited by 11 publications

(4 citation statements)

References 14 publications

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“…Details of the 3D problem formulation are given in Section 5. The solver was validated by computation of several benchmark problems for transonic flow in channels and over wings ( 20 , 21 ) .…”

Section: Methodsmentioning

confidence: 99%

Transonic flow hysteresis in a twin intake model

Kuzmin

2018

Aeronaut. j.

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Turbulent airflow in a supersonic intake model of rectangular cross-section is studied numerically. Instability of shock waves formed in the intake and ahead of the entrance is examined. Solutions of the Reynolds-averaged Navier–Stokes equations are obtained with a finite-volume solver of second-order accuracy. The expulsion and the swallowing of the shocks with a variation of free-stream parameters are studied at both subsonic and supersonic conditions prescribed at the outlet. Hysteresis in the dependence of 2D flow on the free-stream velocity and angle-of-attack is documented. An influence of 3D effects on the flow is examined.

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Section: Methodsmentioning

confidence: 99%

Transonic flow hysteresis in a twin intake model

Kuzmin

2018

Aeronaut. j.

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“…To simulate compressible flow, in addition to continuity and momentum equations, energy equation is also must be solved [15]. In Eq(1) to Eq(3) conservation of mass, momentum and energy for unsteady, viscous and compressible flows were presented, respectively [16]:…”

Section: Governing Equationsmentioning

confidence: 99%

“…Governing equations for SST k-omega models were presented in Eq (15) to Eq(17) [25]: (17) which k S and w S are source terms in the turbulence kinetic energy and turbulence specific dissipation rate equations, respectively. Using turbulence SST k-omega model is recommended for simulation of shear flows and flows which contain shock waves [25].…”

Section: Turbulence Modelingmentioning

confidence: 99%

Numerical study of heat and mass transfer in underexpanded sonic free jet

Adibi¹,

Farhanieh²,

Afshin³

2017

IJHT

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In case of unexpected ruptures in high pressure tanks, choking phenomenon occurs in the cracked area which fluid velocity gets sonic and its pressure exceeds atmospheric pressure. Afterward, pressure of discharged gas quickly changes by crossing through compression and expansion shock waves. The main aim of this study was numerical simulation and investigation of this flow in a 3-step process: (a) Detailed analysis of numerical method, (b) Qualitative and quantitative analysis of velocity, pressure, temperature and turbulence intensity, in order to propose safety strategies and (c) parametric studies on the effects of tank pressure and nozzle geometry on flow structure. In numerical simulations, governing equations (conservation of mass, momentum, energy and equation of state) were discretized based on the finite volume method and flow variables (velocity, pressure, temperature and density) were calculated using density-based algorithm. Validation of numerical method was achieved by comparison with experimental data. The results showed that within 4.4 mm of cracked area, fluid temperature reached to its minimum value of 86 K which would freeze nearby equipment and would make them fragile. Also, parametric studies indicated that inlet pressure had direct relation with exhausted mass flow rate and its maximum occurred in nozzle angle of 3.82 o .

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“…Recently, shock wave instability was revealed in monotonously divergent bent channels (Kuzmin 2015(Kuzmin , 2016. In this case, a shock wave arises due to a concave bend/corner of a wall, whereas its instability is caused by an interaction with the convex bend of the opposite wall.…”

Section: Introductionmentioning

confidence: 99%

Design, fabrication, and performance analysis of a twisted hollow fibre membrane module configuration

Palmarin¹,

Young²,

Lee³

2015

Membr. Water Treat.

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Two-and three-dimensional turbulent airflows in a 9-degrees-bent channel are studied numerically. The inner surfaces of upper and lower walls are parallel to each other upstream and downstream of the bend section. The free stream is supersonic, whereas the flow at the channel exit is either supersonic or subsonic depending on the given backpressure. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver ANSYS CFX. The solutions reveal instability of formed shock waves and a flow hysteresis in considerable bands of the free-stream Mach number at zero and negative angles of attack. The instability is caused by an interaction of shocks with the expansion flow formed over the convex bend of lower wall.

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Shock wave bifurcation in channels with a bend

Cited by 11 publications

References 14 publications

Transonic flow hysteresis in a twin intake model

Transonic flow hysteresis in a twin intake model

Numerical study of heat and mass transfer in underexpanded sonic free jet

Design, fabrication, and performance analysis of a twisted hollow fibre membrane module configuration

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