Determination of surface catalysis on copper oxide in a shock tube using thermochemical nonequilibrium CFD analysis

Yang, Yosheph; Sethuraman, Vignesh Ram Petha; Kim, Hae-Dong; Kim, Jae Gang

doi:10.1016/j.actaastro.2021.12.047

Cited by 8 publications

(2 citation statements)

References 47 publications

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“…( 136) into Eq. ( 137) with P = 1, the final form is written as Many related investigations [129][130][131][132][133] have confirmed that catalytic recombination reactions on the wall can significantly increase the aerothermal load on the surface of vehicles. The diffusive heat flux caused by recombination reactions is the main reason for the increasing aerodynamic heat [132], as shown in Fig.…”

Section: Catalytic Wallmentioning

confidence: 99%

A review of the mathematical modeling of equilibrium and nonequilibrium hypersonic flows

Zhang

Wang

et al. 2022

Adv. Aerodyn.

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This paper systematically reviews the mathematical modeling based on the computational fluid dynamics (CFD) method of equilibrium and nonequilibrium hypersonic flows. First, some physicochemical phenomena in hypersonic flows (e.g., vibrational energy excitation and chemical reactions) and the flow characteristics at various altitudes (e.g., thermochemical equilibrium, chemical nonequilibrium, and thermochemical nonequilibrium) are reviewed. Second, the judgment rules of whether the CFD method can be applied to hypersonic flows are summarized for accurate numerical calculations. This study focuses on the related numerical models and calculation processes of the CFD method in a thermochemical equilibrium flow and two nonequilibrium flows. For the thermochemical equilibrium flow, the governing equations, chemical composition calculation methods, and related research on the thermodynamic and transport properties of air are reviewed. For the nonequilibrium flows, the governing equations that include one-, two-, and three-temperature models are reviewed. The one-temperature model is applied to a chemical nonequilibrium flow, whereas the two- and three-temperature models are applied to a thermochemical nonequilibrium flow. The associated calculations and numerical models of the thermodynamic and transport properties, chemical reaction sources, and energy transfers between different energy modes of the three models are presented in detail. Finally, the corresponding numerical models of two special wall boundary conditions commonly used in hypersonic flows (i.e., slip boundary conditions and catalytic walls) and related research, are reviewed.

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Section: Catalytic Wallmentioning

confidence: 99%

A review of the mathematical modeling of equilibrium and nonequilibrium hypersonic flows

Zhang

Wang

et al. 2022

Adv. Aerodyn.

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“…Using the F–R formula, it is possible to predict the stagnation-point heat flux without solving fluid dynamic equations, which require detailed understanding of the chemical-kinetic processes in hypersonic flows. Several attempts to improve the predictive accuracy of F–R have been made, for example, by adding the influence of surface catalycity (Goulard, 1958; Yang et al , 2022), arbitrary gas mixture effects (Sutton and Garves, 1971), real gas effects at hyper velocity (Olivier, 1995), vibrational temperature in terms of freestream enthalpy (Zuppardi and Verde, 1998), correlating high enthalpy experimental data (De Filippis and Serpico, 1998) and better approximation of the Lewis number effect (Srinivasan et al , 2016).…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Fay and Riddell formula under hypersonic flight conditions

Lee

Yang

Kim

2022

HFF

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Purpose The Fay and Riddell (F–R) formula is an empirical equation for estimating the stagnation-point heat flux on noncatalytic and fully catalytic surfaces, based on an assumption of equilibrium. Because of its simplicity, the F–R has been used extensively for reentry flight design as well as ground test facility applications. This study aims to investigate the uncertainties of the F-R formula by considering velocity gradient, chemical species at the boundary layer edge, and the thermochemical nonequilibrium (NEQ) behind the shock layer under various hypersonic NEQ flow environments. Design/methodology/approach The stagnation-point heat flux calculated with the F–R formula was evaluated by comparison with thermochemical NEQ calculations and existing flight experimental values. Findings The comparisons showed that the F–R underestimated the noncatalytic heat flux, because of the chemical composition at the surface. However, for fully catalytic heat flux, the F–R results were similar to values of surface heat flux from thermochemical NEQ calculations, because the F–R formula overestimates the diffusive heat flux. When compared with the surface heat flux results obtained from flight experimental data, the F–R overestimated the fully catalytic heat flux. The error was 50% at most. Originality/value The results provided guidelines for the F–R calculations under hypersonic flight conditions and for determining the approximate error range for noncatalytic and fully catalytic surfaces.

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Influence of catalytic wall on the effective radius of a blunt body geometry in a nonequilibrium hypersonic flow

Yang

Lee

Kim

2022

Case Studies in Thermal Engineering

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Determination of surface catalysis on copper oxide in a shock tube using thermochemical nonequilibrium CFD analysis

Cited by 8 publications

References 47 publications

A review of the mathematical modeling of equilibrium and nonequilibrium hypersonic flows

A review of the mathematical modeling of equilibrium and nonequilibrium hypersonic flows

Evaluation of Fay and Riddell formula under hypersonic flight conditions

Influence of catalytic wall on the effective radius of a blunt body geometry in a nonequilibrium hypersonic flow

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