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Efficient Modeling and Simulation fo...

Hinkle, Andrew Dale,

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Efficient Modeling and Simulation for the Aerothermal Analysis of Particle-Laden Hypersonic Flows /

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Efficient Modeling and Simulation for the Aerothermal Analysis of Particle-Laden Hypersonic Flows // Andrew Dale Hinkle.
作者:	Hinkle, Andrew Dale,
面頁冊數:	1 electronic resource (179 pages)
附註:	Source: Dissertations Abstracts International, Volume: 85-12, Section: B.
Contained By:	Dissertations Abstracts International85-12B.
標題:	Aerospace engineering. -
電子資源:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31240555
ISBN:	9798383098646

Efficient Modeling and Simulation for the Aerothermal Analysis of Particle-Laden Hypersonic Flows /
Hinkle, Andrew Dale,

Efficient Modeling and Simulation for the Aerothermal Analysis of Particle-Laden Hypersonic Flows /Andrew Dale Hinkle. - 1 electronic resource (179 pages)

Source: Dissertations Abstracts International, Volume: 85-12, Section: B.

Standard approaches for simulating hypersonic flows in particle-laden environments have key limitations in practice, such as high cost and numerical noise. In this work, efficient solution strategies for particle-laden hypersonic flows were developed using both Lagrangian and Eulerian models for the particle phase with the focus on investigating spacecraft surface erosion, as well as convective and radiative heat flux augmentation due to atmospheric particulate encountered during planetary entry.First, an efficient integration strategy for Lagrangian methods, the Trajectory Control Volume (TCV) method, was developed for steady analysis of dilute particle phase problems on general geometries. The TCV method was shown to produce accurate dust impact surface erosion distributions with three orders of magnitude fewer particle samples as compared with Monte Carlo techniques. The TCV approach also enabled the uncertainty quantification of heat-shield dust impact erosion during Mars entry with the non-intrusive polynomial chaos method. The TCV method was extended for analysis of two-way coupled problems and verified for hypersonic flow problems. Application of the technique to a Mars entry case showed that convective heat flux augmentation was insignificant.Besides the TCV approach, a particle phase solver based on an Eulerian model was developed for hypersonic flow problems and used to predict radiation scattering properties for a Mars entry flowfield. A radiation solver based on the P1 spherical harmonics method was used to predict radiative heat flux augmentation due to scattering, which showed little effect for nominal dust loading conditions. Additional augmentation mechanisms were shown to be insignificant for representative Mars and Titan problems.The methods developed in this work provided valuable insight into the aerothermodynamic interactions between the gas and the particle phase for planetary entry missions and are expected to contribute to efficient analysis of particle-laden flows for general hypersonic applications in the future.

English

ISBN: 9798383098646Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Trajectory Control Volume

Efficient Modeling and Simulation for the Aerothermal Analysis of Particle-Laden Hypersonic Flows /
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502 $b Ph.D. $c Missouri University of Science and Technology $d 2024.
520 $a Standard approaches for simulating hypersonic flows in particle-laden environments have key limitations in practice, such as high cost and numerical noise. In this work, efficient solution strategies for particle-laden hypersonic flows were developed using both Lagrangian and Eulerian models for the particle phase with the focus on investigating spacecraft surface erosion, as well as convective and radiative heat flux augmentation due to atmospheric particulate encountered during planetary entry.First, an efficient integration strategy for Lagrangian methods, the Trajectory Control Volume (TCV) method, was developed for steady analysis of dilute particle phase problems on general geometries. The TCV method was shown to produce accurate dust impact surface erosion distributions with three orders of magnitude fewer particle samples as compared with Monte Carlo techniques. The TCV approach also enabled the uncertainty quantification of heat-shield dust impact erosion during Mars entry with the non-intrusive polynomial chaos method. The TCV method was extended for analysis of two-way coupled problems and verified for hypersonic flow problems. Application of the technique to a Mars entry case showed that convective heat flux augmentation was insignificant.Besides the TCV approach, a particle phase solver based on an Eulerian model was developed for hypersonic flow problems and used to predict radiation scattering properties for a Mars entry flowfield. A radiation solver based on the P1 spherical harmonics method was used to predict radiative heat flux augmentation due to scattering, which showed little effect for nominal dust loading conditions. Additional augmentation mechanisms were shown to be insignificant for representative Mars and Titan problems.The methods developed in this work provided valuable insight into the aerothermodynamic interactions between the gas and the particle phase for planetary entry missions and are expected to contribute to efficient analysis of particle-laden flows for general hypersonic applications in the future.
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650 4 $a Physics. $3 516296
650 4 $a Thermodynamics. $3 517304
653 $a Trajectory Control Volume
653 $a Hypersonic flow problems
653 $a Particle-laden environments
653 $a Eulerian model
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690 $a 0348
690 $a 0605
710 2 $a Missouri University of Science and Technology. $b Aerospace Engineering. $e degree granting institution. $3 3829928
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790 $a 0587
791 $a Ph.D.
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