Uncertainty Analysis of Laminar Aeroheating Predictions for Mars Entries

Bose, Deepak; Wright, Michael J.; Palmer, Grant

doi:10.2514/1.20993

Cited by 103 publications

(51 citation statements)

References 17 publications

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“…In an attempt to bound the various catalytic models previously employed, Bose et al . 80 recently developed a simple parametric model that includes two basic catalytic surface reactions:…”

Section: Surface Reactionsmentioning

confidence: 99%

A Review of Aerothermal Modeling for Mars Entry Missions

Wright

Tang

Edquist

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The current status of aerothermal analysis for Mars entry missions is reviewed. The aeroheating environment of all Mars missions to date has been dominated by convective heating. Two primary uncertainties in our ability to predict forebody convective heating are turbulence on a blunt lifting cone and surface catalysis in a predominantly CO2 environment. Future missions, particularly crewed vehicles, will encounter additional heating from shock-layer radiation due to a combination of larger size and faster entry velocity. Localized heating due to penetrations or other singularities on the aeroshell must also be taken into account. The physical models employed to predict these phenomena are reviewed, and key uncertainties or deficiencies inherent in these models are explored.

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“…In an attempt to bound the various catalytic models previously employed, Bose et al . 80 recently developed a simple parametric model that includes two basic catalytic surface reactions:…”

Section: Surface Reactionsmentioning

confidence: 99%

A Review of Aerothermal Modeling for Mars Entry Missions

Wright

Tang

Edquist

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

show abstract

“…See Reference 35 for a discussion of catalysis effects on Mars laminar forebody heating predictions. The primary recombination reactions at the surface are as follows 35 : In flight, these exothermic reactions compete for the O atoms available for recombination. The mechanisms and sensitivities of these reactions are poorly understood and not easily measured.…”

Section: Laminar Cfd Comparisons To Heat Flux Datamentioning

confidence: 99%

Viking Afterbody Heating Computations and Comparisons to Flight Data

Edquist

Wright

Allen

2006

44th AIAA Aerospace Sciences Meeting and Exhibit

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“…As outlined in a recent review article on the status of aerothermal modeling [2], such data is very limited and contains large uncertainties. While lower and upper bounds on heating rates are certainly useful, depending on the flight conditions and atmosphere, these predictions can differ significantly [3]. An example of experimental data obtained on RCG coated Space Shuttle tiles [4] is shown below in Fig.…”

Section: Introduction and Existing State-of-the-artmentioning

confidence: 99%

A Finite-Rate Gas-Surface Interaction Model Informed by Fundamental Computational Chemistry Simulations

Schwartzentruber¹

2013

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information A -Approved for public release A finite-rate gas-surface model (for use as a CFD boundary condition) specific to oxygen-silica reactions was formulated using computational chemistry calculations. A new interatomic potential was developed (and made publicly available) specifically for oxygen-silica gas-surface reactions (ReaxFF-SiO-GSI) using a large database of density functional theory single point energies.Computational chemistry calculations predicted a number of surface defects on realistic silica surfaces (in agreement with experimental data) which participate in the surface recombination of oxygen. The dominant reaction pathways occurring on these defects were studied by MD simulations of oxygen impacts. Steric factors and activation energies were computed for each reaction and the resulting model was formulated to satisfy detailed balance. The dominant mechanisms were found to not be activated processes (no energy barriers), resulting in little temperature dependence on recombination efficiencies. Product molecules resulting from a single collision-based reaction were found to not thermally accommodate to the surface, rather they leave in excited vibrational levels. The new finite-rate model and thermal accommodation results can be directly used in CFD calculations.

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Uncertainty Analysis of Laminar Aeroheating Predictions for Mars Entries

Cited by 103 publications

References 17 publications

A Review of Aerothermal Modeling for Mars Entry Missions

A Review of Aerothermal Modeling for Mars Entry Missions

Viking Afterbody Heating Computations and Comparisons to Flight Data

A Finite-Rate Gas-Surface Interaction Model Informed by Fundamental Computational Chemistry Simulations

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