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A Quantitative Analysis of Finite-Ra...

Mussoni, Erin Elizabeth,

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A Quantitative Analysis of Finite-Rate Surface Ablation Models for Hypersonic Flight /

Record Type:	Electronic resources : Monograph/item
Title/Author:	A Quantitative Analysis of Finite-Rate Surface Ablation Models for Hypersonic Flight // Erin Elizabeth Mussoni.
Author:	Mussoni, Erin Elizabeth,
Description:	1 electronic resource (190 pages)
Notes:	Source: Dissertations Abstracts International, Volume: 86-04, Section: B.
Contained By:	Dissertations Abstracts International86-04B.
Subject:	Aerospace engineering. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31334394
ISBN:	9798384485070

A Quantitative Analysis of Finite-Rate Surface Ablation Models for Hypersonic Flight /
Mussoni, Erin Elizabeth,

A Quantitative Analysis of Finite-Rate Surface Ablation Models for Hypersonic Flight /Erin Elizabeth Mussoni. - 1 electronic resource (190 pages)

Source: Dissertations Abstracts International, Volume: 86-04, Section: B.

During hypersonic flight, a vehicle heat shield encounters harsh aerothermal environments and undergoes complex surface chemical and physical processes that impact its mass loss, shape change, and surface heating responses. Thermal protection system design requires credible ablation models that describe the gas-surface interactions under these extreme conditions. An uncertainty quantification methodology was implemented to characterize legacy and recently developed air/carbon surface ablation models for nonequilibrium high-enthalpy flow conditions.Validation assessments compared model predictions of carbon monoxide, a primary ablation product, quantities in the boundary layer with measured laser absorption spectrometry data. Experiments were conducted at the hypersonic reflected shock tunnel at Sandia National Laboratories. Simulations were performed to model the graphite cylindrical test articles that were preheated to surface temperatures ranging from 1250-2150 K for 4 km/s freestream conditions. Sensitivity analyses assessed the influence of epistemic reaction rate uncertainties on predicted gas species quantities at the surface and in the boundary layer. Dominant rate uncertainties were propagated through the model to quantify the comparison error between predicted and measured carbon monoxide quantities. Results show near agreement between finite-rate and equilibrium model predictions, which overpredict carbon monoxide number density for analyzed experimental conditions.An approach to identify reaction- and diffusion-limited ablation regimes through a Damköhler analysis is employed to compare ablation model predictions between 3 and 4 km/s freestream shock tunnel test conditions. The predicted surface ablation regimes for each test condition agree with observed ablation rate trends between finite-rate and equilibrium models. Companion sensitivity analyses further characterized model behavior differences by identifying dominant reaction rate and chemical pathways in predicting gas species quantities for each test case. The demonstrated analysis framework enables researchers to interrogate complex models to understand potential chemical pathways as part of the ablation process. It also provides a flexible validation methodology as more experimental data becomes available and models continue to be developed and matured.

English

ISBN: 9798384485070Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Ablation

A Quantitative Analysis of Finite-Rate Surface Ablation Models for Hypersonic Flight /
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245 1 2 $a A Quantitative Analysis of Finite-Rate Surface Ablation Models for Hypersonic Flight / $c Erin Elizabeth Mussoni.
264 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2024
300 $a 1 electronic resource (190 pages)
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500 $a Source: Dissertations Abstracts International, Volume: 86-04, Section: B.
500 $a Advisors: Delplanque, Jean-Pierre Committee members: Robinson, Stephen; Shaw, Benjamin; Wagnild, Ross.
502 $b Ph.D. $c University of California, Davis $d 2024.
520 $a During hypersonic flight, a vehicle heat shield encounters harsh aerothermal environments and undergoes complex surface chemical and physical processes that impact its mass loss, shape change, and surface heating responses. Thermal protection system design requires credible ablation models that describe the gas-surface interactions under these extreme conditions. An uncertainty quantification methodology was implemented to characterize legacy and recently developed air/carbon surface ablation models for nonequilibrium high-enthalpy flow conditions.Validation assessments compared model predictions of carbon monoxide, a primary ablation product, quantities in the boundary layer with measured laser absorption spectrometry data. Experiments were conducted at the hypersonic reflected shock tunnel at Sandia National Laboratories. Simulations were performed to model the graphite cylindrical test articles that were preheated to surface temperatures ranging from 1250-2150 K for 4 km/s freestream conditions. Sensitivity analyses assessed the influence of epistemic reaction rate uncertainties on predicted gas species quantities at the surface and in the boundary layer. Dominant rate uncertainties were propagated through the model to quantify the comparison error between predicted and measured carbon monoxide quantities. Results show near agreement between finite-rate and equilibrium model predictions, which overpredict carbon monoxide number density for analyzed experimental conditions.An approach to identify reaction- and diffusion-limited ablation regimes through a Damköhler analysis is employed to compare ablation model predictions between 3 and 4 km/s freestream shock tunnel test conditions. The predicted surface ablation regimes for each test condition agree with observed ablation rate trends between finite-rate and equilibrium models. Companion sensitivity analyses further characterized model behavior differences by identifying dominant reaction rate and chemical pathways in predicting gas species quantities for each test case. The demonstrated analysis framework enables researchers to interrogate complex models to understand potential chemical pathways as part of the ablation process. It also provides a flexible validation methodology as more experimental data becomes available and models continue to be developed and matured.
546 $a English
590 $a School code: 0029
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Chemistry. $3 516420
650 4 $a Thermodynamics. $3 517304
650 4 $a Mechanical engineering. $3 649730
653 $a Ablation
653 $a Aerothermodynamics
653 $a Finite-rate processes
653 $a Nonequilibrium flows
653 $a Uncertainty quantification
690 $a 0538
690 $a 0485
690 $a 0348
690 $a 0548
710 2 $a University of California, Davis. $b Mechanical and Aerospace Engineering. $e degree granting institution. $3 3818623
720 1 $a Delplanque, Jean-Pierre $e degree supervisor.
773 0 $t Dissertations Abstracts International $g 86-04B.
790 $a 0029
791 $a Ph.D.
792 $a 2024
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31334394