Uncertainty Analysis of Mars Entry Flows Over Hypersonic Inflatable Aerodynamic Decelerators
Abstract
A comprehensive uncertainty analysis for high-fidelity flowfield simulations over a fixed aeroshell of Hypersonic Inflatable Aerodynamic Decelerator scale for Mars entry is presented for fully laminar and turbulent flows at peak stagnation-point heating conditions. This study implements a sparse-collocation approach for efficient and accurate uncertainty quantification in the high-fidelity numerical modeling of hypersonic reentry flow simulations, which may contain large numbers of aleatory and epistemic uncertainties.
Recommended Citation
A. J. Brune et al., "Uncertainty Analysis of Mars Entry Flows Over Hypersonic Inflatable Aerodynamic Decelerators," Proceedings of the 11th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, AIAA AVIATION Forum (2014, Atlanta, GA), American Institute of Aeronautics and Astronautics (AIAA), Jun 2014.
The definitive version is available at https://doi.org/10.2514/6.2014-2672
Meeting Name
11th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, AIAA AVIATION Forum (2014: Jun. 16-20, Atlanta, GA)
Department(s)
Mechanical and Aerospace Engineering
Research Center/Lab(s)
Center for High Performance Computing Research
Document Type
Article - Conference proceedings
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2014 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
Publication Date
01 Jun 2014
