Large eddy simulation of a turbulent channel flow using dynamic Smagorinsky subgrid scale model and differential equation wall model

Hoque, Mohammad Azizul; Mallik, Muhammad Saiful Islam; Hossain, Muhammad Sajjad; Gope, Rathindra Chandra; Uddin, Md.Ashraf

doi:10.1016/j.ijft.2024.100676

Cited by 2 publications

(1 citation statement)

References 16 publications

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“…The finite volume method (FVM) is used to discretize N-S governing equation, where the spatial inviscid flux is discretized using the Roe flux difference splitting scheme (FDS) of the second-order upwind scheme, and time is explicitly advanced using the Runge Kutta. The LES-Smagorinsky-Lilly turbulence model is used to numerically calculate the flow field of the hypersonic inlet (Giuliano 2024;Hoque et al 2024). The density-based solver and the transient calculations are adopted.…”

Section: Calculation Scheme and Boundary Conditionsmentioning

confidence: 99%

Numerical analysis on the MHD flow control of the hypersonic vehicle inlet

Li,

Huang,

Zhu

2024

Preprint

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Under the assumption of the low magnetic Reynolds number, the coupled model of the turbulent flow field and the electromagnetic field is established to simulate the flow characteristics of Weakly Ionized Gas (WIG) in the inlet under the MHD (Magnetohydrodynamic) effect. Results show that WIG has more active thermodynamic properties than that of air in inlet. Specifically, at the throat, the thermal conductivity of WIG is augmented by 1.64 times compared to that of air. For the inlet with an MHD acceleration zone, the separation shock waves will be fallen on the third ramp and converted into the reattachment shock waves here. And the separation bubbles generated by the reattachment shock waves are weakened due to the multiple reflections before entering the isolator, hence, the wall pressure and the skin friction coefficient have a decrease in the isolator. Nevertheless, in the inlet with an MHD deceleration zone, the separation shock waves will be fallen precisely at the throat under the effect of the countercurrent Lorentz force, so that the separation shock waves are directly transformed into reattachment shock waves at the throat and all reflected into the isolator, which leads to the peak manifestation of the wall pressure and the skin friction coefficient in the isolator.

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Section: Calculation Scheme and Boundary Conditionsmentioning

confidence: 99%

Numerical analysis on the MHD flow control of the hypersonic vehicle inlet

Li,

Huang,

Zhu

2024

Preprint

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Analysis of the Effect of Sampling Probe Geometry on Measurement Accuracy in Supersonic Gas Flow

Zhang,

Chen,

et al. 2024

Aerospace

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The accuracy of sampling of gas components has a significant impact on the measurement of various performance parameters in the combustion chamber of an aero-engine. In order to investigate the effect of the probe geometry of a six-point gas sampling probe on sampling accuracy in supersonic gas flow, a three-dimensional probe gas flow characteristic solution model is established through numerical simulation methods of components of transport and fluid–solid coupling. Probes with three angles of 28°, 30°, and 32° and an optimized conical probe are constructed. The sampling accuracy of the probes with different geometries is compared and evaluated by the deviation of the component volume fraction before and after sampling and the resulting combustion efficiency error. This paper presents a set of calculation methods for solving the relative deviation of volume fraction by an iterative method based on the ideal gas law and the Redlich–Kwong equation (R-K equation). The method is designed to solve the exact component volume fraction problem in the simulation calculation. The study results demonstrate that the 28° and optimized conical probes improve sampling accuracy more effectively than the original 30° structure. The deviation of the volume fractions of the two structures is less than 1.7%, and the combustion efficiency error is less than 0.09%. The developed iterative calculation method can significantly reduce the theoretical calculation error to less than 0.06%. The experimental data of the test bench are in good agreement with the simulation results, thereby demonstrating the reliability and accuracy of the sampling probe following structural optimization.

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Large eddy simulation of a turbulent channel flow using dynamic Smagorinsky subgrid scale model and differential equation wall model

Cited by 2 publications

References 16 publications

Numerical analysis on the MHD flow control of the hypersonic vehicle inlet

Numerical analysis on the MHD flow control of the hypersonic vehicle inlet

Analysis of the Effect of Sampling Probe Geometry on Measurement Accuracy in Supersonic Gas Flow

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