A fast algorithm to solve viscous two-phase flow in an axisymmetric rocket nozzle

Mehta, R. C.; Jayachandran, T.

doi:10.1002/(sici)1097-0363(19980315)26:5<501::aid-fld642>3.0.co;2-u

Cited by 13 publications

(8 citation statements)

References 10 publications

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“…The time dependent strategy is used to integrate the equations temporally by a two-stage Runge-Kutta method. It should be noted that the steady-state solution is required in the present study, and the time accuracy is of no importance ( Mehta and Jayachandran, 1998;Slater and Young, 2001;Saito, 2002 ). The steady state is reached when the gas flow structures and the penetration height vary little with the integrations, and the solution is supposed to be converged.…”

Section: Discussionmentioning

confidence: 96%

Numerical simulations of spray jet in supersonic crossflows using an Eulerian approach with an SMD model

Liu

Guo

Wang

2016

International Journal of Multiphase Flow

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Section: Discussionmentioning

confidence: 96%

Numerical simulations of spray jet in supersonic crossflows using an Eulerian approach with an SMD model

Liu

Guo

Wang

2016

International Journal of Multiphase Flow

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“…To establish the reliability of these formulations, a numerical analysis of the nozzle designed by the Jet Propulsion Laboratory (JPL), which is widely used for validation of nozzle flow analysis calculations, was performed. We compared our results with existing simulated [22] and experimental [23] data. The working fluid inside the nozzle was assumed to be air, and the initial pressure and temperature were set to P 0 = 1 0342 MPa and T 0 = 555K, respectively.…”

Section: Code Validationmentioning

confidence: 99%

The Effects of Heat Shielding in Jet Engine Exhaust Systems on Aircraft Survivability

Baek

Kim

et al. 2014

Numerical Heat Transfer, Part A: Applications

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The infrared signatures from hot engine parts pose major threats to military aircraft survivability. Reducing the skin temperature at the rear of the fuselage is key to reducing susceptibility to heat-seeking armaments. A heat shield placed between the nozzle wall and the outer casing of the engine can decrease the skin temperature at the rear of the fuselage. Therefore, numerical modeling of the fluid flow fields coupled with the radiative and conductive processes within the heat shield, nozzle, and casing were performed to determine the temperature distribution at the rear of the fuselage. The effect of the material properties and the dimensions of the heat shield were studied in order to determine their effects on the susceptibility of an aircraft.

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“…Several researchers have analyzed the problem and data is available for comparison [83][84][85][86][87][88][89][90][91][92]. In most of the reported studies, a shorter diverging section, in comparison with the one considered here, has been used when predicting the two-fluid flow.…”

Section: Problem 4: Inviscid Transonic Dusty Flow In a Converging-divmentioning

confidence: 99%

“…where f D is the ratio of the drag coefficient C D to the stokes drag C D0 =24/Re P and is given by The heat transferred from gas to particle phase per unit volume is given as [88] ( ) …”

Section: Problem 4: Inviscid Transonic Dusty Flow In a Converging-divmentioning

confidence: 99%

The Geometric Conservation Based Algorithms For Multi-Fluid Flow At All Speeds

Moukalled¹

2002

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)American University of Beirut ME Dept. PO Box: 11-0236 Beirut Lebanon PERFORMING ORGANIZATION REPORT NUMBERN/A SPONSOR/MONITOR'S ACRONYM(S) 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)EOARD PSC 802 BOX 14 FPO 09499-0014 SPONSOR/MONITOR'S REPORT NUMBER(S)SPC 01-4005 DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTThis report results from a contract tasking American University of Beirut as follows: The proposed work involves implementing and (thoroughly) testing the Geometric Conservation Based family of Algorithms within a structured finite-volume framework. The convection terms along the control volume faces will be evaluated using a High Resolution scheme applied within the context of the Normalized Variable Formulation methodology. In order to accelerate the convergence rate and reduce the overall computational cost of the algorithm, the outer iterations will be accelerated by using a non-linear full multigrid method. The discretization scheme will be second-order accurate in space and first order accurate in time (even though extension to second order accuracy should be straightforward). The newly implemented algorithms will be tested by solving a variety of two-dimensional multi-fluid flow problems in the subsonic, transonic, and supersonic regimes. Examples include: 1) Phase separation in a duct (water-air); 2) Turbulent bubbly flow in a pipe; 3) Turbulent gas-solid flow in a curved duct; 4) Dusty flow over a flat plate at subsonic flow conditions (~incompressible); 5) Dusty flow in a converging-diverging nozzle, and 6) Any problem of interest to Dr. Sekar (AFRL/PR). A detailed report describing the work will be submitted at end of contract as specified in the schedule of supplies in the submitted proposal. SUBJECT TERMS AbstractThis work is concerned with the implementation and testing, within a structured collocated finite-volume framework, of seven segregated algorithms for the prediction of multi-phase flow at all speeds. These algorithms belong to the Geometric Conservation Based Algorithms

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A fast algorithm to solve viscous two-phase flow in an axisymmetric rocket nozzle

Cited by 13 publications

References 10 publications

Numerical simulations of spray jet in supersonic crossflows using an Eulerian approach with an SMD model

Numerical simulations of spray jet in supersonic crossflows using an Eulerian approach with an SMD model

The Effects of Heat Shielding in Jet Engine Exhaust Systems on Aircraft Survivability

The Geometric Conservation Based Algorithms For Multi-Fluid Flow At All Speeds

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