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Experimental and numerical study of the Mars Pathfinder vehicle

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Title: Experimental and numerical study of the Mars Pathfinder vehicle
Authors: Bur, R.1 reynald.bur@onera.fr, Benay, R.1, Chanetz, B.1, Galli, A.1, Pot, T.1, Hollis, B.2, Moss, J.2
Source: Aerospace Science & Technology. Oct2003, Vol. 7 Issue 7, p510. 7p.
Subjects: Space vehicles, Hypersonic wind tunnels, United States. National Aeronautics & Space Administration
Geographic Terms: United States
Abstract: An experimental and numerical study on the Mars Pathfinder aeroshell vehicle has been carried out in the framework of an agreement between ONERA and NASA. The experimental work was performed in the ONERA R5Ch hypersonic wind tunnel. Flowfield visualizations and heat-flux measurements along the model have been obtained. Numerical simulations have been performed at ONERA with the Reynolds-Averaged Navier–Stokes (RANS) solver NASCA and at NASA with a Direct Simulation Monte Carlo (DSMC) code. The flowfield structure is correctly reproduced by both computations. The location of the bow shock is well predicted, as well as the expansion waves emanating from the end of the forebody cone. Both computations also predict the same extension of the separation bubble in the base flow region of the model. Measured and calculated heat-flux distributions along the model have been compared. Both computations give similar results, except for the prediction of the heat-flux level on the afterbody cone. But computations overpredict the measured heat-flux values on the forebody and the model sting: the value of the stagnation point is overestimated at 28% and the average sting level at 35%. [Copyright &y& Elsevier]
Copyright of Aerospace Science & Technology is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
Database: Engineering Source
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Header DbId: egs
DbLabel: Engineering Source
An: 10926873
AccessLevel: 6
PubType: Academic Journal
PubTypeId: academicJournal
PreciseRelevancyScore: 0
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  Data: Experimental and numerical study of the Mars Pathfinder vehicle
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  Data: <searchLink fieldCode="JN" term="%22Aerospace+Science+%26+Technology%22">Aerospace Science & Technology</searchLink>. Oct2003, Vol. 7 Issue 7, p510. 7p.
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  Data: <searchLink fieldCode="DE" term="%22Space+vehicles%22">Space vehicles</searchLink><br /><searchLink fieldCode="DE" term="%22Hypersonic+wind+tunnels%22">Hypersonic wind tunnels</searchLink><br /><searchLink fieldCode="DE" term="%22United+States%2E+National+Aeronautics+%26+Space+Administration%22">United States. National Aeronautics & Space Administration</searchLink>
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  Data: An experimental and numerical study on the Mars Pathfinder aeroshell vehicle has been carried out in the framework of an agreement between ONERA and NASA. The experimental work was performed in the ONERA R5Ch hypersonic wind tunnel. Flowfield visualizations and heat-flux measurements along the model have been obtained. Numerical simulations have been performed at ONERA with the Reynolds-Averaged Navier–Stokes (RANS) solver NASCA and at NASA with a Direct Simulation Monte Carlo (DSMC) code. The flowfield structure is correctly reproduced by both computations. The location of the bow shock is well predicted, as well as the expansion waves emanating from the end of the forebody cone. Both computations also predict the same extension of the separation bubble in the base flow region of the model. Measured and calculated heat-flux distributions along the model have been compared. Both computations give similar results, except for the prediction of the heat-flux level on the afterbody cone. But computations overpredict the measured heat-flux values on the forebody and the model sting: the value of the stagnation point is overestimated at 28% and the average sting level at 35%. [Copyright &y& Elsevier]
– Name: AbstractSuppliedCopyright
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  Data: <i>Copyright of Aerospace Science & Technology is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
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        Value: 10.1016/S1270-9638(03)00062-2
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        Text: English
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      – SubjectFull: United States. National Aeronautics & Space Administration
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              Text: Oct2003
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