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Vasilevskii, E. B.; Осипцов, А. Н.; Chirikhin, A. V.; Yakovleva, L. V.

doi:10.1023/a:1013996332270

Cited by 33 publications

(2 citation statements)

References 7 publications

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“…It is evident that they affect the load on the heat shield during entry. Recent investigations have shown that the presence of small particles (with the size of a micrometer or fractions of a micrometer) in a hypersonic flow may cause a significant increase of the heat flux to the front surface of a probe even if the particles have low mass concentration [4].…”

Section: Introductionmentioning

confidence: 99%

“…= dimensionless collision integral ratio C d = drag force coefficient c i = molar concentration of species i, mol∕cm 3 D p = effective particle diameter, m D n = particle average diameter, m E p = particle energy source term, J∕m 3 s F = inviscid/viscous fluxes; kg∕m 2 s; : : : ; N · s∕m 2 s; : : : ; J∕m 2 s F p;cell = momentum source term in a cell, N F x;y;z;p = particle momentum source terms, J∕m 3 s f d = drag force, N f n = number frequency g = degeneracy H t = volume specific total enthalpy, J∕m 3 s h = mass specific enthalpy, J∕kg h L = latent heat of evaporation, J∕kg i, j, k, l = species M rel = relative Mach number N u = Nusselt number with rarefaction effects N u 0 = Nusselt number for continuum region n = number density, 1∕m 3 _ n = numbers of particles in cell per unit time, 1∕s P = particle position P [1][2][3][4] = position vectors p t = total pressure, N∕m 2 Q c = convective heat flux, W∕m 2 Q c-v = chemical-vibrational energy exchange term, J∕m 3 s Q e-v = electron-vibration energy exchange term, J∕m 3 s _ Q net = rate of net heat transfer, W∕m 2 Q r = radiative heat flux, W∕m 2 Q t-v = translational-vibrational energy exchange term, J∕m 3 s Q v-v = vibration-vibration energy exchange term, J∕m 3 s q = source term; kg∕m 3 ; : : : ; N · s∕m 3 ; : : : ; J∕m 3 q c;cell = convective heat flux in a cell, N Re rel = relative Reynolds number S 0 = standard entropy, J∕mol · K _ T rate = rate of temperature change, K∕s V = total velocity, m∕s V = volume of a cell, m 3 X = solution vector; kg∕m 3 ; : : : ; N · s∕m 3 ; : : : ; J∕m 3 λ = coefficient of thermal conductivity, W∕mK τ = relaxation time, s…”

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Two-Phase Flow Solver for Hypersonic Entry Flows in a Dusty Martian Atmosphere

Majid

Bauder

Herdrich

et al. 2016

Journal of Thermophysics and Heat Transfer

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The occurrence of global dust storms on Mars is one of the most spectacular meteorological events in the solar system. The following question arises: What influence might dust particles have on the heat flux onto a heat shield of a planetary probe entering the Martian atmosphere? For the numerical simulation of such an entry, the sequential iterative nonequilibrium algorithm program previously developed at the Institut für Raumfahrtsysteme is used. A five-species model (CO 2 , O 2 , CO, O, and C) is implemented in the code. The Euler-Lagrangian approach is used for the modeling and simulation of the solid dust particles in the hypersonic entry flow. An adequate model for the drag force computation is implemented. The heat transfer model of the particles consists of convective heating and radiation cooling. With these models, heat fluxes onto the heat shield of the Mars sample return orbiter spacecraft due to impingement of particles are computed and compared with the convective heat fluxes from the continuum flowfield for the exemplary conditions of test case 3. From these simulations, it is found that the ratio of heat flux due to impingement of the particles compared to convective heat flux of the flowfield gas is very low. However, particles with larger radii may generate significant heat fluxes and erosion on the wall of the particle.

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Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

Two-Phase Flow Solver for Hypersonic Entry Flows in a Dusty Martian Atmosphere

Majid

Bauder

Herdrich

et al. 2016

Journal of Thermophysics and Heat Transfer

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Computation of hypersonic viscous flows with the thermally perfect gas model using a discontinuous Galerkin method

Ching

Bensassi

et al. 2022

Numerical Methods in Fluids

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This article is concerned with the numerical simulation of high‐speed thermally perfect flows using high‐order discontinuous Galerkin (DG) methods. In these methods, the polynomial approximation of the solution is susceptible to spurious oscillations, especially in high‐gradient regions. The introduction of variable thermodynamic properties, important for hypersonic flows, can exacerbate this issue. Given the general lack of satisfactory high‐order DG simulations of these types of flows, our primary objective is to demonstrate the success of the formulation proposed here in computing flows in this regime. Secondary goals are to (a) highlight that DG schemes are significantly less sensitive than finite‐volume methods to mesh‐shock misalignment in the given setting and (b) evaluate the sensitivity of surface heating predictions to various types of no‐slip isothermal wall boundary conditions. To handle strong shocks prevalent in this flow regime, intra‐element solution variations are used to detect discontinuities and smooth artificial viscosity is employed for stabilization. We discuss the algorithmic developments for extending a standard DG discretization of the compressible Navier–Stokes equations with the calorically perfect gas model to the thermally perfect gas model. We apply the resulting DG formulation to several hypersonic test cases, including inviscid flow over a cylinder and viscous flow over a double cone. Where appropriate, our results are benchmarked against those obtained with state‐of‐the‐art finite‐volume hypersonic flow solvers. The final case entails high‐speed particle‐laden flow over a blunt body. The results of this test illuminate how the consideration of variable thermodynamic properties influences the prediction of the particle phase.

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Effect of a Dispersed Admixture on the Flow Pattern and Heat Transfer in a Supersonic Dusty-Gas Flow Around a Cylinder

Volkov¹,

Tsirkunov²

2005

Fluid Dyn

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A mathematical model of two-phase (gas-solid particle) flow which takes into account particle-particle collisions and the feedback effect of the admixture on the gas parameters is proposed. The dispersed phase is described by a kinetic equation of the Boltzmann type and the carrier gas by modified Navier-Stokes equations. Using this model, a supersonic uniform dusty-gas flow past a cylinder is calculated. The fields of the macroparameters of the admixture and the carrier medium are obtained. The dependence of the heat transfer at the stagnation point on the relative particle size and the freestream admixture concentration is studied in detail. The ranges of these parameters on which particle collisions and the feedback effect of the admixture on the carrier-gas flow are important are found.

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Cited by 33 publications

References 7 publications

Two-Phase Flow Solver for Hypersonic Entry Flows in a Dusty Martian Atmosphere

Two-Phase Flow Solver for Hypersonic Entry Flows in a Dusty Martian Atmosphere

Computation of hypersonic viscous flows with the thermally perfect gas model using a discontinuous Galerkin method

Effect of a Dispersed Admixture on the Flow Pattern and Heat Transfer in a Supersonic Dusty-Gas Flow Around a Cylinder

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