Mars Pathfinder Rarefied Aerodynamics: Computations and Measurements

James, Nicolas; Robert, C Blanchard; Richard, G Wilmoth; Robert, D Braun

doi:10.2514/2.3475

Cited by 46 publications

(18 citation statements)

References 13 publications

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“…for c y > 0; (6) Brought to you by | Western University Authenticated Download Date | 6/7/15 9:47 PM where V x1 and V x2 are two unknown functions of time t and the single distance variable y.…”

Section: The Physical Problem and Mathematical Formulationmentioning

confidence: 99%

“…A significantly large number of flows may be classified within the transition regime (0:1 < Kn < 10). Relevant applications within a rarefied gas include upper atmospheric simulations [2], such as the Space Shuttle Orbiter [3], the Magellan Spacecraft [4], the Stardust Sample Return Capsule [5], and the Mars Pathfinder [6]. Additional relevance outside that of upper-atmospheric studies includes chemical vapor deposition [7], the micro filter [8], and micro-electro mechanical systems (MEMS) [9][10][11][12].…”

Section: Introductionmentioning

confidence: 99%

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Kinetic and thermodynamic treatment for the exact solution of the unsteady Rayleigh flow problem of a rarefied homogeneous charged gas

Wahid

2012

Journal of Non-Equilibrium Thermodynamics

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This article presents an exact and enhanced solution of the study in the previous paper [Can. J. Phys., 88 (2010), 501-511]. For this purpose, I use the traveling wave solution method instead of the small parameter method, which enables us to have the full exact solution without any cut-off from the value of variables. In addition, I use the accurate formula of the electronelectron collision frequency. I persist in avoiding the discontinuity in the solution caused by the Laplace transformation results, which is included in the previous study. In the present work, the kinetic and the irreversible thermodynamic properties of the charged gas are presented from the molecular viewpoint. Our study is based on the solution of the BGK (BhatnagerGross-Krook) model of the Boltzmann kinetic equation, with the precision value of the electron-electron collision frequency. The BGK model equation coupled with Maxwell's equations for electrons near a moving rigid plane are solved. The distinction and comparisons between the perturbed and the equilibrium velocity distribution functions are illustrated. The ratios between the different contributions of the internal energy changes are predicted via the extended Gibbs equation for both diamagnetic and paramagnetic plasmas. The results are applied to a typical model of laboratory argon plasma.

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Section: The Physical Problem and Mathematical Formulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Kinetic and thermodynamic treatment for the exact solution of the unsteady Rayleigh flow problem of a rarefied homogeneous charged gas

Wahid

2012

Journal of Non-Equilibrium Thermodynamics

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“…Similar comparisons for the drag coefficient indicated that the DSMC results were not inconsistent with the measurements, although the flight data were only taken in the continuum regime, and so direct comparison with DSMC was not possible. An extensive aerodynamics database was constructed using G2 and DAC for the Mars Pathfinder mission by Moss et al [79]. The DSMC analyses traversed a Knudsen number range from 100 to 0.027 and angle of attack variation from 0 to 35 deg.…”

Section: Analyses Of Planetary Entry Flowsmentioning

confidence: 99%

Computation of Hypersonic Flows Using the Direct Simulation Monte Carlo Method

Boyd

2015

Journal of Spacecraft and Rockets

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The direct simulation Monte Carlo method has evolved over 50 years into a powerful numerical technique for the computation of complex, nonequilibrium gas flows. In this context, "nonequilibrium" means that the velocity distribution function is not in an equilibrium form due to a low number of intermolecular collisions within a fluid element. In hypersonic flow, nonequilibrium conditions occur at high altitude and in regions of flowfields with small length scales. In this paper, the theoretical basis of the direct simulation Monte Carlo technique is discussed. In addition, the methods used in direct simulation Monte Carlo are described for simulation of high-temperature, real gas effects and gas-surface interactions. Several examples of the application of direct simulation Monte Carlo to flows around blunt hypersonic vehicles are presented to illustrate current capabilities. Areas are highlighted where further research on the direct simulation Monte Carlo technique is required. Nomenclature A= surface element of area, m 2 C = particle velocity vector, m∕s e r = specific rotational energy, J∕kg f = probability density function g = relative velocity, m∕s Kn = Knudsen number k = Boltzmann's constant, J∕kg L = characteristic length scale, m m = mass of a particle, kg N = average number of particles in a cell N p = number of particles in a cell N t = number of iterations n = number density, m −3 P c = collision probability r = particle position vector, m T = temperature, K t = time, s V = cell volume, m 3 Δf = rate of change due to collision processes ε act = activation energy, J ε r = rotational energy, J ε tot = total collision energy, J λ = mean free path, m ζ = number of rotational degrees of freedom σ = collision cross section, m 2 τ r = rotational relaxation time, s ω = viscosity temperature exponent

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“…Similar comparisons for the drag coefficient indicated that the DSMC results were not inconsistent with the measurements although the flight data were only taken in the continuum regime so direct comparison with DSMC was not possible. An extensive aerodynamics database was constructed using G2 and DAC for the Mars Pathfinder mission by Moss et al [74]. The DSMC analyses traversed a Knudsen number range from 100 to 0.027 and angle of attack variation from 0 to 35 deg..…”

Section: Dsmc Analyses Of Planetary Entry Flowsmentioning

confidence: 99%

Computation of Hypersonic Flows Using the Direct Simulation Monte Carlo Method

Boyd

2013

21st AIAA Computational Fluid Dynamics Conference

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The direct simulation Monte Carlo method (DSMC) has evolved over 50 years into a powerful numerical technique for the computation of complex, nonequilibrium gas flows. In this context, nonequilibrium means that the velocity distribution function is not in an equilibrium form due to a low number of intermolecular collisions within a fluid element. In hypersonic flow, nonequilibrium conditions occur at high altitude and in regions of flow fields with small length scales. In this article, the theoretical basis of the DSMC technique is discussed. In addition, the methods used in DSMC are described for simulation of high temperature, real gas effects and gas-surface interactions. Several examples of the application of DSMC to flows around blunt hypersonic vehicles are presented to illustrate current capabilities.

show abstract

Mars Pathfinder Rarefied Aerodynamics: Computations and Measurements

Cited by 46 publications

References 13 publications

Kinetic and thermodynamic treatment for the exact solution of the unsteady Rayleigh flow problem of a rarefied homogeneous charged gas

Kinetic and thermodynamic treatment for the exact solution of the unsteady Rayleigh flow problem of a rarefied homogeneous charged gas

Computation of Hypersonic Flows Using the Direct Simulation Monte Carlo Method

Computation of Hypersonic Flows Using the Direct Simulation Monte Carlo Method

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