Benchmarking a New, Open-Source Direct Simulation Monte Carlo (DSMC) Code for Hypersonic Flows

Ahmad, Abdul Ossman; Scanlon, Thomas; Reese, Jason M.

doi:10.1007/978-3-642-25685-1_164

Cited by 3 publications

(2 citation statements)

References 7 publications

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“…Transient adaptive subcells (TAS) are employed to automatically adjust the number of collision cells, i.e. cells wherein collision partners are chosen, corresponding to the local gas density gradients 55 56 57 . Subcell sizes are calculated such that on average there are two particles in each subcell.…”

Section: Dsmc Methods and Solvermentioning

confidence: 99%

Thermally induced gas flows in ratchet channels with diffuse and specular boundaries

Shahabi

Baier

Roohi

et al. 2017

Sci Rep

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A net gas flow can be induced in the gap between periodically structured surfaces held at fixed but different temperatures when the reflection symmetry along the channel axis is broken. Such a situation arises when one surface features a ratchet structure and can be augmented by altering the boundary conditions on different parts of this surface, with some regions reflecting specularly and others diffusely. In order to investigate the physical mechanisms inducing the flow in this configuration at various Knudsen numbers and geometric configurations, direct simulation Monte Carlo (DSMC) simulations are employed using transient adaptive subcells for collision partner selection. At large Knudsen numbers the results compare favorably with analytical expressions, while for small Knudsen numbers a qualitative explanation for the flow in the strong temperature inhomogeneity at the tips of the ratchet is provided. A detailed investigation of the performance for various ratchet geometries suggests optimum working conditions for a Knudsen pump based on this mechanism.

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Section: Dsmc Methods and Solvermentioning

confidence: 99%

Thermally induced gas flows in ratchet channels with diffuse and specular boundaries

Shahabi

Baier

Roohi

et al. 2017

Sci Rep

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“…[64,83] Since its release, it has been tested for both speed and accuracy, with satisfying results. [84,85,86] Following the work of prior multi-region and coupled OpenFOAM solvers, development of hybrid particle-continuum schemes started almost immediately after the release of dsmcFoam. [87,88,89] Despite these improvements in parallelism and hybridization, the computational cost of using a full DSMC solver is too great to be used during a simulation, and is not included in this thesis' code.…”

Section: Openfoam Is a Toolbox (Written In C++) For Numerical Solversmentioning

confidence: 99%

Open Source Toolkit for Reentry Object Modeling

Ostrom

Lloyd

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Open Source Toolkit for Reentry Object ModelingChristopher L. Ostrom II Predicting the mass, position, and velocity of an object during its reentry are critical to satisfy NASA and ESA requirements. This thesis outlines a 3-D orbit and mass determination system for use on low earth orbit as applicable to general objects, of various material and size. The solution uses analytical models to calculate heat flux and aerodynamic drag, with some basic numerical models for simple orbit propagation and mass flow rate due to ablation. The system outlined in this thesis currently provides a framework for rough estimates of demise altitude and final mass, but also allows for many potential accuracy and speed improvements. 77 aerospace materials were tested, in solid spheres, cubes, and cylinders; it was found that materials with low latent heat of fusion (less than 10

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Error quantification among CFD solvers for high-speed, non-adiabatic, wall-bounded turbulent flows.

Hussain

Hickey

Godbolt

et al. 2021

AIAA Scitech 2021 Forum

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Benchmarking a New, Open-Source Direct Simulation Monte Carlo (DSMC) Code for Hypersonic Flows

Cited by 3 publications

References 7 publications

Thermally induced gas flows in ratchet channels with diffuse and specular boundaries

Thermally induced gas flows in ratchet channels with diffuse and specular boundaries

Open Source Toolkit for Reentry Object Modeling

Error quantification among CFD solvers for high-speed, non-adiabatic, wall-bounded turbulent flows.

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