Multi-Fidelity Modeling for Efficient Aerothermal Prediction of Deployable Re-Entry Vehicles
The objective of this work was to investigate a multi-fidelity modeling approach to accurately and efficiently predict the aerothermal response of a large diameter deployable hypersonic re-entry vehicle in Mars entry. A co-Kriging based multi-fidelity modeling approach was developed that utilized several refinements including LU-decomposition for parallelization, distance weighted root mean square error adaptive sampling, and surface distribution parameterization using Hicks-Henne bump functions. Several computational tools of varying fidelity were investigated to model the surface heat flux, shear stress, and pressure in the multi-fidelity modeling process. The LAURA CFD software with thermochemical nonequilibrium and with calorically perfect gas models were used as high and low-fidelity tools, respectively, to model laminar convective heat flux, surface pressure, and shear stress. A second low-fidelity tool investigated utilized the Sutton-Graves equation with surface correlations by Krasnov for the convective heat flux, and the modified Newtonian method for surface pressure. The multi-fidelity model was found to have a mean convective heat rate error of 4.6%, a mean pressure force error of 0.81%, and a mean shear force error of 2.86% when compared to high-fidelity CFD simulations. Compared to a Kriging model of the high-fidelity data only, the multi-fidelity model required approximately one-half the number of high-fidelity model evaluations to obtain the same accuracy level. The computational cost of constructing and evaluating the multi-fidelity model were approximately one and five orders of magnitude less, respectively, than one high-fidelity model simulation.
M. Santos et al., "Multi-Fidelity Modeling for Efficient Aerothermal Prediction of Deployable Re-Entry Vehicles," Proceedings of the 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference (2018, Orlando, FL), American Institute of Aeronautics and Astronautics (AIAA), Sep 2018.
The definitive version is available at https://doi.org/10.2514/6.2018-5268
22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference (2018: Sep. 17-19, Orlando, FL)
Mechanical and Aerospace Engineering
Center for High Performance Computing Research
Keywords and Phrases
Computational fluid dynamics; Errors; Heat convection; Hypersonic aerodynamics; Hypersonic vehicles; Interpolation; Mean square error; Reentry; Shear stress, Computational tools; High fidelity models; Hypersonic re-entry; Multi-fidelity modeling; Orders of magnitude; Root mean square errors; Surface distributions; Surface heat fluxes, Heat flux
International Standard Book Number (ISBN)
Article - Conference proceedings
© 2018 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Sep 2018