Hypersonic Propulsion-breaking the Thermal Barrier

Weidner, J. P.

doi:10.1243/pime_proc_1993_207_246_02

Cited by 4 publications

(3 citation statements)

References 10 publications

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“…Flux of atoms recombining at the surface Flux of atoms impinging on the surface (1) which is defined as the ratio of the impinging atoms that recombine at the surface over the total impinging atoms on the surface. It is notable that the Eley-Rideal (E-R) and Langmuir-Hinshelwood (L-H) recombination mechanisms are the two dominant mechanisms in the surface catalysis recombination process [63].…”

Section: Methodsmentioning

confidence: 99%

“…As the flying speed increases, the extreme aeroheating brings the problem of the “heat barrier”, which is the major barrier for the next generations of high-speed aircraft [ 1 , 2 ]. An in-depth understanding of how aerothermal heat is generated and how to accurately predict the amount of heat produced is of paramount importance for designing reliable thermal protection systems (TPS) [ 3 , 4 , 5 ].…”

Section: Introductionmentioning

confidence: 99%

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Sensitivity Analysis of the Catalysis Recombination Mechanism on Nanoscale Silica Surfaces

Cui

Sun

et al. 2022

Nanomaterials

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A deep understanding of surface catalysis recombination characteristics is significant for accurately predicting the aeroheating between hypersonic non-equilibrium flow and thermal protection materials, while a de-coupling sensitivity analysis of various influential factors is still lacking. A gas–solid interface (GSI) model with a hyperthermal flux boundary was established to investigate the surface catalysis recombination mechanisms on nanoscale silica surfaces. Using the reactive molecular dynamics (RMD) simulation method, the effects of solid surface temperature, gas incident angle, and translational energy on the silica surface catalysis recombination were qualified under hyperthermal atomic oxygen (AO), atomic nitrogen (AN), and various AN/AO gas mixtures’ influence. It can be found that, though the Eley–Rideal (E–R) recombination mechanism plays a dominant role over the Langmuir–Hinshelwood (L–H) mechanism for all the sensitivity analyses, a non-linear increasing pattern of AO recombination coefficient γO2 with the increase in incident angle θin and translational energy Ek is observed. Compared with the surface catalysis under hyperthermal AO impact, the AN surface adsorption fraction shows an inverse trend with the increase in surface temperature, which suggests the potential inadequacy of the traditional proportional relationship assumptions between the surface adsorption concentration and the surface catalysis recombination coefficient for other species’ impact instead of AOs. For the incoming bi-component AO/AN gas mixtures, the corresponding surface catalysis coefficient is not the simple superposition of the effects of individual gases but is affected by both the intramolecular bond energies (e.g., O2, N2) and intermolecular energies (e.g., Si/N, Si/O).

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Section: Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Sensitivity Analysis of the Catalysis Recombination Mechanism on Nanoscale Silica Surfaces

Cui

Sun

et al. 2022

Nanomaterials

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“…Although the great potentials of hypersonic vehicles for military strategy and space exploration are well recognized, there remain many "unaware unknowns" or "aware unknowns" [2] that need to be solved, such as "blackout" [3] and "thermal barrier" [4]. The space shuttle Columbia crashed in a severe aerodynamic thermal environment during its reentry from orbit in 2003 [2], leading to the recognition that the study of aerodynamic heating is a critical problem that cannot be bypassed on the road of hypersonic flight.…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Thermodynamic and Chemical Kinetic Models for Hypersonic and High-Temperature Flow Simulation

Zhao,

Yang,

Wang

et al. 2023

Applied Sciences

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Significant thermochemical nonequilibrium effects always exist in the flow field around hypersonic vehicle at extreme flight condition. Previous studies have proposed various thermodynamic and chemical kinetic models to describe the thermochemical nonequilibrium processes in hypersonic and high-temperature flow. However, different selections from such models might lead to remarkable variations in computational burden and prediction accuracy, which is still a matter of being unclear. In the present study, different commonly studied models for calculating the thermochemical nonequilibrium are systematically evaluated. The 5-, 7- and 11-species chemical kinetic models of Dunn-Kang, Gupta and Park together with the one- and two-temperature models are employed respectively to simulate the hypersonic flows over a standard cylinder with the radius of 1 m by HyFLOW, which is a commercial software based on the numerical solution of Navier-Stokes equations. Three flight conditions of FIRE Ⅱ classical flight trajectory are employed in the study. It shows that the differences between the results of the Dunn-Kang, Gupta and Park chemical kinetic models with the same number of species are small, but the Gupta model predicts the most conservative values of the wall heat flux. When only the order of magnitude and distribution trends of the pressure and wall heat flux are concerned, the one-temperature model combined with 5-species chemical reaction model can be used for a rapid prediction. While the accurate flow solution is required, the two-temperature model conjugated with Gupta 11-species model is recommended, especially at the conditions of extremely high altitude and Mach number.

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Experimental and Computational Study of Flow Interactions in a Generic Scramjet Inlet-Isolator

Idris

Saad

Zare‐Behtash

et al. 2015

29th International Symposium on Shock Waves 2

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Hypersonic Propulsion-breaking the Thermal Barrier

Cited by 4 publications

References 10 publications

Sensitivity Analysis of the Catalysis Recombination Mechanism on Nanoscale Silica Surfaces

Sensitivity Analysis of the Catalysis Recombination Mechanism on Nanoscale Silica Surfaces

Evaluation of Thermodynamic and Chemical Kinetic Models for Hypersonic and High-Temperature Flow Simulation

Experimental and Computational Study of Flow Interactions in a Generic Scramjet Inlet-Isolator

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