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Modeling of Shock Tunnel Aeroheating Data on the Mars Science Laboratory Aeroshell

Wright, Michael J. and Olejniczak, Joe and Brown, James L. and Hornung, Hans G. and Edquist, Karl T. (2006) Modeling of Shock Tunnel Aeroheating Data on the Mars Science Laboratory Aeroshell. Journal of Thermophysics and Heat Transfer, 20 (4). pp. 641-651. ISSN 0887-8722. https://resolver.caltech.edu/CaltechAUTHORS:WRIjtht06

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Abstract

A series of shots are run in the T5 shock tunnel at California Institute of Technology to measure heating levels on a 70 blunt cone at angle of attack in an environment representative of the Mars Science Laboratory entry. Twenty shots are obtained in CO₂ over a range of enthalpies and pressures chosen to span the laminar and turbulent flow regimes. The data indicate that the lee side turbulent heating augmentation predicted by flight simulations is valid and must be accounted for during the design of the thermal protection system. Computational fluid dynamic simulations are generally in good agreement with the laminar data when employing a supercatalytic wall model, whereas turbulent simulations are in reasonable agreement when a noncatalytic wall model is used. The reasons for this discrepancy are unknown at this time. The turbulent heating augmentation is shown to be inversely related to freestream enthalpy. Changes in angle of attack between 11 and 16 are shown to have minimal impact on measured and computed heating. A transition criterion based on momentum thickness Reynolds number, analogous to that used in flight predictions, predicts onset with reasonable accuracy, although transition is observed to occur later than the current design criterion indicates.


Item Type:Article
Related URLs:
URLURL TypeDescription
http://dx.doi.org/10.2514/1.19896DOIArticle
ORCID:
AuthorORCID
Hornung, Hans G.0000-0002-4903-8419
Additional Information:This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. Presented as Paper 0177 at the 43rd Aerospace Sciences Meeting and Exhibit, Reno, NV, 10–13 January 2005; received 5 September 2005; revision received 13 November 2005; accepted for publication 16 November 2005. Support for this work was provided to NASA Ames and Langley Research Centers by the Mars Technology Program in support of the Mars Science Laboratory mission. The California Institute of Technology was funded by the Jet Propulsion Laboratory under contract No. JPL PO #1256067. The authors would like to thank Jeff Umland (Jet Propulsion Laboratory) for his support, as well as Dan Reda (Ames) and Brian Hollis (Langley) for discussions on turbulent transition criteria in flight and ground test facilities.
Group:GALCIT
Funders:
Funding AgencyGrant Number
JPL1256067
Issue or Number:4
Record Number:CaltechAUTHORS:WRIjtht06
Persistent URL:https://resolver.caltech.edu/CaltechAUTHORS:WRIjtht06
Official Citation:Modeling of Shock Tunnel Aeroheating Data on the Mars Science Laboratory Aeroshell Michael J. Wright, Joe Olejniczak, James L. Brown, Hans G. Hornung, and Karl T. Edquist Journal of Thermophysics and Heat Transfer 2006 20:4, 641-651
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:11299
Collection:CaltechAUTHORS
Deposited By: Archive Administrator
Deposited On:29 Jul 2008 22:31
Last Modified:29 Jan 2020 23:36

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