Large eddy simulation of supersonic, compressible, turbulent mixing layers

Arora, Konark; Chakravarthy, V. Kalyana; Chakraborty, Debasis

doi:10.1016/j.ast.2019.01.034

Cited by 25 publications

(5 citation statements)

References 40 publications

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“…By using finite volume code, 2D and 3D simulations for the LES supersonic mixing layer is introduced. The simulations results are compared with experimental DNS and LES results, both with 2D and 3D, where 3D analysis shows better results [6].…”

Section: Literature Reviewmentioning

confidence: 99%

Performance Analysis of Supersonic Combustion Chamber using Planar-Shaped Strut Injector

Roga

2023

Preprint

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Significant researches have been enthusiastic throughout the last centuries for supersonic and hypersonic flight conditions for enabling flights many times faster than sound. This current work presents the performance analysis of supersonic combustor interface and flow construction through a scramjet engine with a Planar-shaped strut injector (PSSI) at the supersonic Mach. An important aspect of this study is the discovery of the fuel mixing mechanism inside the combustion chamber with PSSI. Mixing and combustion performance can be enhanced by the novel PSSI configuration. The scramjet configuration is incorporated with the supersonic inlet air temperature of 1250 K, where the vitiated air follows at Mach 3, and this technique is based on a high accelerating effect of scramjet propulsion mechanism. Scramjet engines can maintain a naturalistic high enthalpy conditions in minimum durations. It is observed that the maximum temperature of 3510 K is attained at the recirculating zones that are produced because of undulation enlargement and therefore the fuel jet losses concentration whereas the maximum combustion efficiency of 86% is investigated from the current research work.

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Section: Literature Reviewmentioning

confidence: 99%

Performance Analysis of Supersonic Combustion Chamber using Planar-Shaped Strut Injector

Roga

2023

Preprint

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“…Use NX10 to model the geometric structure [3], and simulate the actual working state of the rectangular nozzle as much as possible, and construct the external free fluid domain. The fluid domain adopts Workbench adaptive meshing, and the boundary layer is encrypted.…”

Section: Simulation Model and Parameter Establishmentmentioning

confidence: 99%

Analysis of Flow Pattern of Turbulent Boundary Layer Jet in Rectangular Nozzle

Lyu

2022

J. Phys.: Conf. Ser.

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The design of the rectangular nozzle affects the thrust and stealth performance of the propeller. The relationship between the outlet area and the jet flow pattern is studied through the simulation analysis of three different outlet area rectangular nozzles with an aspect ratio of 8. From the simulation results, it can be seen that the exit area under a single variable determines the value and range of the jet Mach number, which produces a huge change in the mixing zone of the turbulent boundary layer, but it has nothing to do with the development trend of the near and far field.

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“…Use NX10 to model the geometric structure, and simulate the working state of Laval nozzle as much as possible, and construct the external free fluid domain [3][4][5][6]. The fluid domain adopts Workbench adaptive meshing, and the boundary layer is encrypted.…”

Section: Simulation Model and Parameter Establishmentmentioning

confidence: 99%

Analysis of Turbulent Boundary Layer Jet Flow Pattern of Laval Nozzle

Lyu

2022

J. Phys.: Conf. Ser.

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The rationality of the structure design of the Laval nozzle directly affects its work efficiency. The simulation software is used to simulate and analyze the structure and operating conditions of the Laval nozzle, and to find the relationship between the change of the turbulent boundary layer jet flow pattern. From the simulation results, it can be seen that the outlet diameter under a single variable cannot directly determine the value and range of the jet Mach number, but it produces a huge change in the mixing zone of the turbulent boundary layer, which directly affects the turbulent kinetic energy.

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Large eddy simulation of supersonic, compressible, turbulent mixing layers

Cited by 25 publications

References 40 publications

Performance Analysis of Supersonic Combustion Chamber using Planar-Shaped Strut Injector

Performance Analysis of Supersonic Combustion Chamber using Planar-Shaped Strut Injector

Analysis of Flow Pattern of Turbulent Boundary Layer Jet in Rectangular Nozzle

Analysis of Turbulent Boundary Layer Jet Flow Pattern of Laval Nozzle

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