Doctoral Dissertations

Keywords and Phrases

Aerothermodynamics; Co-Kriging; Deployable Entry Systems; Multifidelity Modeling


“NASA is developing deployable entry technologies in the form of the Hypersonic Inflatable Aerodynamic Decelerator (HIAD) and the Adaptable Deployable Entry Technology (ADEPT) vehicles to support human exploration of Mars. To ensure that these technologies are reliable under uncertain entry conditions and extreme aerothermal environments, uncertainty quantification must be integrated into the design process which typically requires large number of high-fidelity computational fluid dynamics (CFD) simulations with prohibitively high computational cost. To address this challenge, construction of multi-fidelity aerothermal response predictions which combine low-fidelity correlations with fewer high-fidelity CFD models in a way that produces highly accurate surrogates with reduced computational cost were investigated in this research. The primary objective of this research was to develop and validate a co-Kriging based multi-fidelity (CKMF) surrogate modeling approach for the prediction of the aerothermal response of deployable entry technologies in Mars entry. The CKMF modeling approach developed utilized several refinements that included Lower- Upper correlation matrix decomposition for use with parallel processing, distance weighted root mean square error adaptive sampling, and surface distribution parameterization using Hicks-Henne bump functions. The multi-fidelity approach was applied to the aerothermal prediction of axisymmetric HIAD vehicles with surface scalloping and non-axisymmetric ADEPT vehicles over a range of flight conditions and vehicle nose radii. The developed CKMF models were shown to produce accurate and computationally efficient surrogate models of the laminar convective heat flux (3% maximum error), turbulent convective heat flux (8% maximum error), and radiative heat flux (10% maximum error) throughout the entire design space. The computational cost of building the CKMF models was shown to be significantly less than the cost of creating a surrogate of the high-fidelity model only. Additionally, the cost to evaluate the multi-fidelity model was shown to be four to five orders of magnitude less than the cost to evaluate the high-fidelity model”--Abstract, page iv.


Hosder, Serhat

Committee Member(s)

Riggins, David W.
Han, Daoru Frank
Isaac, Kakkattukuzhy M.
West, Thomas K.


Mechanical and Aerospace Engineering

Degree Name

Ph. D. in Aerospace Engineering


This work was supported by a NASA Space Technology Research Fellowship (NSTRF) under grant no. 80NSSC17K0170.


Missouri University of Science and Technology

Publication Date

Summer 2021

Journal article titles appearing in thesis/dissertation

  • Multifidelity Modeling for Efficient Aerothermal Prediction of Deployable Entry Vehicles
  • Multifidelity Turbulent Heating Prediction of Hypersonic Inflatable Aerodynamic Decelerators with Surface Scalloping
  • Multifidelity Heating Prediction of Adaptable, Deployable Entry Placement Technology Vehicles


xiv, 132 pages

Note about bibliography

Includes bibliographic references.


© 2021 Mario Santos, All rights reserved.

Document Type

Dissertation - Open Access

File Type




Thesis Number

T 11921

Electronic OCLC #