Hypersonic and High-Temperature Gas Dynamics, Second Edition

Anderson, J. D.

doi:10.2514/4.861956

Cited by 933 publications

(628 citation statements)

References 152 publications

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“…To avoid such heating, con¦gurations such as those reported in Fig. 1 have been proposed considering that the radiative heat §ux is linearly dependent on the geometrical radius of the vehicle nose [5].…”

Section: Vehicle Configuration Selectionmentioning

confidence: 99%

“…Global transport properties of the gas mixture rely on semiempirical rules such as Wilke£s mixing rule for viscosity and thermal conductivity [5]. The viscosity and thermal conductivity of the ith species is obtained by Kinetic Theory of gases [5]. For the di¨usion coe©cient of the ith species in the mixture, the multicomponent di¨usion coe©cient is applied, where species mass di¨usivity is evaluated by Kinetic Theory [5].…”

Section: Design Analysis Based On Computational Fluid Dynamicsmentioning

confidence: 99%

“…Indeed, due to broader stability characteristics of the implicit formulation, a converged steady-state solution can be obtained much faster using the implicit formulation rather than the explicit one. Global transport properties of the gas mixture rely on semiempirical rules such as Wilke£s mixing rule for viscosity and thermal conductivity [5]. The viscosity and thermal conductivity of the ith species is obtained by Kinetic Theory of gases [5].…”

Section: Design Analysis Based On Computational Fluid Dynamicsmentioning

confidence: 99%

“…Several methods, typical of hypersonics, are available such as those derived from Newtonian, Modi¦ed Newtonian, and Prandtl Mayer theories [5]. In order to predict viscous contribution to aerodynamic forces and moments, the shear force is determined on each vehicle panel on the assumption of a laminar or turbulent §at plate [9].…”

Section: Engineering-based Design Analysismentioning

confidence: 99%

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Nonequilibrium computational flowfield analysis for the design of mars manned entry vehicles

Viviani

Pezzella

2013

Progress in Flight Physics

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This paper deals with the aerodynamic exploration analysis of innovative unusual vehicle concepts, suitable for a manned Mars entry, aiming to support design studies of planetary entry systems. In this framework, two lifting body (LB) con¦gurations have been analyzed so far. Several fully three-dimensional (3D) computational §uid dynamics (CFD) analyses, both for a perfect gas model and for a nonequilibrium reacting gas mixture model, have been performed. The §ow¦eld environment past the exploration vehicle for an assigned Mars entry scenario has been addressed. To this end, a wide range of §ow conditions, including di¨erent angles of attack (AoA), various Mach numbers, and Reynolds numbers, have been investigated. Results reported in the paper are useful for providing numerical data for further understanding the §uid dynamics processes, as those of high enthalpy §ow and vehicle shape e¨ects, involved in the design analysis of LB vehicles for the exploration of Mars.

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Section: Vehicle Configuration Selectionmentioning

confidence: 99%

Section: Design Analysis Based On Computational Fluid Dynamicsmentioning

confidence: 99%

Section: Design Analysis Based On Computational Fluid Dynamicsmentioning

confidence: 99%

Section: Engineering-based Design Analysismentioning

confidence: 99%

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Nonequilibrium computational flowfield analysis for the design of mars manned entry vehicles

Viviani

Pezzella

2013

Progress in Flight Physics

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“…In some cases, proper treatment of reactions is needed to accurately predict overall shock thickness, standoff, and heat transfer. 1 In other cases, such as when reactants are minor species, the overall flow field is not affected by details of the reaction model, but a particular radiation signature may be strongly affected. 2 A case of the latter situation is the subject of the present study, and allows for a detailed examination of several issues important to chemical reaction models for rarefied, high-speed flows.…”

Section: Introductionmentioning

confidence: 99%

Chemical reaction modeling for hypervelocity collisions between O and HCl

2007

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The sensitivity of a rarefied-to-transitional flow to the fidelity of the chemical reaction model is investigated for a new molecular dynamics/quasiclassical trajectory (MD/QCT)-derived model and compared with the widely used total collision energy (TCE) model of Bird. For hypervelocity collisions that occur in the space environment, it is not clear, a priori, that the TCE model will provide reasonable results for the required high energy range and, particularly, if strong favoring of the reaction among different forms of reactant energy occurs. In fact, in previous work, the TCE model, using available Arrhenius parameters, has been found, for these flow conditions, to give unphysical probabilities. A chemical reaction model, suitable for use in the direct simulation Monte Carlo (DSMC) method, is developed to simulate the hypervelocity collisions of O(P3)+HCl(Σ+1)→OH(Π2)+Cl(P2), an example of an important reaction in high-altitude atmospheric-jet interactions. The model utilizes the MD/QCT method with a new benchmark triplet A″ surface. Since the modeling of chemical reactions in DSMC simulations requires the use of a reaction probability, the adequacy of the overall collision cross section, usually modeled by the variable hard sphere (VHS) model, is also considered. To obtain an accurate collision cross section, the approach of Tokumasu and Matsumoto was used in the MD/QCT method with the aforementioned potential energy surface. Energy transfer between the target HCl translational and internal energy modes was investigated and it was found that the variation of the inelastic cross section has a negligible effect on the transport cross section. Therefore, a MD/QCT VHS equivalent collision cross section was obtained and along with the MD/QCT reaction cross sections were utilized in the full DSMC calculation of the flow field. It was found that for a low enthalpy reaction, in hypervelocity collisions, the TCE model with accurate Arrhenius rates appears to agree well with the rigorous MD/QCT calculations which shows that the reaction does not exhibit strong favoring.

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Missile Guidance

Rodriguez

2015

Wiley Encyclopedia of Electrical and Electronics Engineering

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Hypersonic and High-Temperature Gas Dynamics, Second Edition

Cited by 933 publications

References 152 publications

Nonequilibrium computational flowfield analysis for the design of mars manned entry vehicles

Nonequilibrium computational flowfield analysis for the design of mars manned entry vehicles

Chemical reaction modeling for hypervelocity collisions between O and HCl

Missile Guidance

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