Implicit gas-kinetic unified algorithm based on multi-block docking grid for multi-body reentry flows covering all flow regimes

Peng, Ao‐Ping; Li, Zhihui; Wu, Junlin; Jiang, Xinyu

doi:10.1016/j.jcp.2016.09.050

Cited by 59 publications

(26 citation statements)

References 77 publications

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“…In order to validate the present DSMC modeling rules for simulating weakly inhomogeneous flow in simple gases, the planar Couette shear flow from two parallel infinite plates with relative motion placed at a distance of H is simulated and compared with the results of the gas-kinetic unified algorithm (GKUA) [23][24][25][26][27] where we directly solve the Boltzmann-type velocity distribution function equation. The Couette flow is a simple and benchmark boundary-value flow problem.…”

Section: Computational Test Of Dsmc Modeling On Controlling Statisticmentioning

confidence: 99%

“…Ground test facilities can hardly reproduce the crucial non-equilibrium flows of extremely highspeed reentry in non-continuum atmospheric environment [10]. Although kinetic methods including the direct solver of kinetic models [11][12][13][14][15], the discrete velocity models [16][17][18][19][20][21][22], the gas-kinetic unified algorithm [23][24][25][26][27], the unified flow solver [28,29], and the BGK-type discrete unified gas-kinetic schemes [30,31] can describe non-equilibrium gas flows, they are still under development and computationally expensive for hypersonic flows. Currently, the most widely used method for rarefied hypersonic flows is the Direct Simulation Monte Carlo (DSMC) [32][33][34] method.…”

Section: Introductionmentioning

confidence: 99%

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DSMC modeling of rarefied ionization reactions and applications to hypervelocity spacecraft reentry flows

Fang

Liang

et al. 2020

Adv. Aerodyn.

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The DSMC modeling is developed to simulate three-dimensional (3D) rarefied ionization flows and numerically forecast the communication blackout around spacecraft during hypervelocity reentry. A new weighting factor scheme for rare species is introduced, whose key point is to modify the corresponding chemical reaction coefficients involving electrons, meanwhile reproduce the rare species in resultants and preserve/delete common species in reactants according to the weighting factors. The resulting DSMC method is highly efficient in simulating weakly inhomogeneous flows including the Couette shear flow and controlling statistical fluctuation with high resolution. The accurate reliability of the present DSMC modeling is also validated by the comparison with a series of experimental measurements of the Shenzhou reentry capsule tested in a low-density wind tunnel from the HAI of CARDC. The obtained electron number density distribution for the RAM-C II vehicle agrees well with the flight experiment data, while the electron density contours for the Stardust hypervelocity reentry match the reference data completely. In addition, the present 3D DSMC algorithm can capture distribution of the electron, N + and O + number densities better than the axis-symmetric DSMC model. The introduction of rare species weighting factor scheme can significantly improve the smoothness of the number density contours of rare species, especially for that of electron in weak ionization case, while it has negligible effect on the macroscopic flow parameters. The ionization characteristics of the Chinese lunar capsule reentry process are numerically analyzed and forecasted in the rarefied transitional flow regime at the flying altitudes between 80 and 97 km, and the simulations predict communication blackout altitudes which are in good agreement with the actual reentry flight data. For the spacecraft reentry with hypervelocity larger than the second cosmic speed, it is forecasted and verified by the present DSMC modeling that ionization reactions will cover the windward capsule surface, leading to reentry communication blackout, and the communication interruption must be considered in the communication design during reentry in rarefied flow regimes.

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Section: Computational Test Of Dsmc Modeling On Controlling Statisticmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

DSMC modeling of rarefied ionization reactions and applications to hypervelocity spacecraft reentry flows

Fang

Liang

et al. 2020

Adv. Aerodyn.

Self Cite

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“…This case investigates the relaxation of this highly nonequilibrium distribution function. The truncated discrete velocity space is [− 26,26] in each direction with 260 discrete points (260*260*260 mesh). The iteration time ∆t is chosen as 0.001τ .…”

Section: Relaxation Of Bi-model Distribution Function (0d-3v Case)mentioning

confidence: 99%

Conservative discrete-velocity method for the ellipsoidal Fokker-Planck equation in gas-kinetic theory

et al. 2019

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A conservative discrete velocity method (DVM) is developed for the ellipsoidal Fokker-Planck (ES-FP) equation in prediction of non-equilibrium neutral gas flows in this paper. The ES-FP collision operator is solved in discrete velocity space in a concise and quick finite difference framework. The conservation problem of discrete ES-FP collision operator is solved by multiplying each term in it by extra conservative coefficients whose values are very closed to unity. Their differences to unity are in the same order of the numerical error in approximating the ES-FP operator in discrete velocity space. All the macroscopic conservative variables (mass, momentum and energy) are conserved in the present modified discrete ES-FP collision operator. Since the conservation property in discrete element of physical space is very important for numerical scheme when discontinuity and large gradient exist in flow field, a finite volume framework is adopted for the transport term of ES-FP equation. For nD-3V (n < 3) cases, a nD-quasi nV reduction is specially proposed for ES-FP equation and the corresponding FP-DVM method, which can greatly reduce the computational cost. The validity and accuracy of both ES-FP equation and FP-DVM method are examined using a series of 0D-3V homogenous relaxation cases and 1D-3V shock structure cases with different M ach numbers, in which 1D-3V cases are reduced to 1D-quasi 1V cases. Both the predictions of 0D-3V and 1D-3V cases match well with the benchmark results such as analytical Boltzmann solution, direct full-Boltzmann numerical solution and DSMC result. Especially, the FP-DVM predictions match well with the DSMC results in the M ach 8.0 shock structure case, which is in high non-equilibrium, and is a challenge case of the model Boltzmann equation and the corresponding numerical methods.

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“…On the other hand, the LBE and GKS, with implicit and explicit Chapman-Enskog approximations, respectively, are designed mainly for continuum flows, and therefore are also inadequate for multiscale flow simulations. Some UP schemes, which aim to capture flow behaviors in all regimes, have also been developed in the past decade [18][19][20][21][22][23][24]. Particularly, the finite-volume unified gas-kinetic scheme (UGKS) [18] has gained much attention due to its special reconstruction of cell-interface flux, in which the analytical time evolved integral solution of the kinetic equation is adopted to approximate the distribution function at cell-interface.…”

Section: Introductionmentioning

confidence: 99%

Progress of discrete unified gas-kinetic scheme for multiscale flows

Guo

2021

Adv. Aerodyn.

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Multiscale gas flows appear in many fields and have received particular attention in recent years. It is challenging to model and simulate such processes due to the large span of temporal and spatial scales. The discrete unified gas kinetic scheme (DUGKS) is a recently developed numerical approach for simulating multiscale flows based on kinetic models. The finite-volume DUGKS differs from the classical kinetic methods in the modeling of gas evolution and the reconstruction of interface flux. Particularly, the distribution function at a cell interface is reconstructed from the characteristic solution of the kinetic equation in space and time, such that the particle transport and collision effects are coupled, accumulated, and evaluated in a numerical time step scale. Consequently, the cell size and time step of DUGKS are not passively limited by the particle mean-free-path and relaxation time. As a result, the DUGKS can capture the flow behaviors in all regimes without resolving the kinetic scale. Particularly, with the variation of the ratio between numerical mesh size scale and kinetic mean free path scale, the DUGKS can serve as a self-adaptive multiscale method. The DUGKS has been successfully applied to a number of flow problems with multiple flow regimes. This paper presents a brief review of the progress of this method.

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Implicit gas-kinetic unified algorithm based on multi-block docking grid for multi-body reentry flows covering all flow regimes

Cited by 59 publications

References 77 publications

DSMC modeling of rarefied ionization reactions and applications to hypervelocity spacecraft reentry flows

DSMC modeling of rarefied ionization reactions and applications to hypervelocity spacecraft reentry flows

Conservative discrete-velocity method for the ellipsoidal Fokker-Planck equation in gas-kinetic theory

Progress of discrete unified gas-kinetic scheme for multiscale flows

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