An assessment of OpenFOAM solver on RANS simulations of round supersonic free jets

Zang, Bin; Us, Vevek; Lim, H. D.; Wei, Xiaofeng; New, T. H.

doi:10.1016/j.jocs.2018.07.002

Cited by 32 publications

(15 citation statements)

References 57 publications

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“…For the present baseline supersonic jet configuration, Wu and New [20] observed that perfect jet expansion occurs at NPR=3.4. Lastly, while the initial baseline nozzle wall boundary layer was not measured during the study, simulations conducted by Zang et al [23] on the same nozzle, jet apparatus and flow condition at NPR=4 indicated that they are most likely to be turbulent here.…”

Section: Jet Operating Conditionsmentioning

confidence: 94%

“…Apparently, the parameter β is insufficient to evaluate shock strengths when the shock structures are altered by asymmetric nozzle geometries (such as the stepped nozzles used here). Furthermore, quantitative information on shock strengths obtained through experimental measurements are rather limited, and this lack of quantitative experimental data has compelled many studies to compare between numerical simulation results to qualitative schlieren visualization [20,23,44]. One of the reasons for the lack of experimental data on shock strengths is due to the limitations of conventional experimental techniques.…”

Section: Quantitative Calibrated Schlierenmentioning

confidence: 99%

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Mitigation of under-expanded supersonic jet noise through stepped nozzles

Wei

Mariani

Chua

et al. 2019

Journal of Sound and Vibration

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Section: Jet Operating Conditionsmentioning

confidence: 94%

Section: Quantitative Calibrated Schlierenmentioning

confidence: 99%

Mitigation of under-expanded supersonic jet noise through stepped nozzles

Wei

Mariani

Chua

et al. 2019

Journal of Sound and Vibration

Self Cite

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“…In the first method, the Navier-Stokes equations are averaged according to Reynolds (in compressible flows, according to Favre). The advantages are mean requirements for the computing resources (including due to the possibility of obtaining a solution in twodimensional plane or axisymmetric formulations) and the solution satisfactory accuracy in the region of the first jet "barrel" [12,[14][15][16].…”

Section: Numerical Calculationmentioning

confidence: 99%

Flow Feature in Supersonic Non-Isobaric Jet near the Nozzle Edge

2022

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Using the example of studying the supersonic underexpanded jet initial section, the issue of interpreting the experimental visualization data and Pitot pressure measurement data using the results of numerical calculations (2d RANS k-ω SST) is discussed. It is shown that the gradient S-shaped feature of the gas-dynamic structure near the nozzle exit, observed in the form of a barrel shock, is a characteristic that separates the expansion and compression regions, and downstream is transformed into a barrel shock. It has been established that the reason for the observed S-shaped curvature of this feature is the axisymmetric nature of the jet flow.

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“…Mesh refinement was applied along the jet core and shear layers, such that the estimated y+ at the nozzle exit based on the exit velocity was approximately 3. A detailed assessment of the present RANS simulations has been reported in a recent study by Zang et al (2018), where both mesh independence check and validation with available experimental measurements were carried out.…”

Section: Numerical Simulationmentioning

confidence: 99%