Abstract
This paper proposes two novel multi-fidelity neural network architectures tailored for high-dimensional inputs such as computational flow fields. The proposed methods are compared with the multi-fidelity deep neural networks from the literature using a 2-dimensional flow-varying supercritical airfoil problem. The main objective of this study is to generate a multi-fidelity prediction of aerodynamic coefficients using pressure coefficient fields around the airfoil. To generate the dataset, a coarse grid is solved using SU2 Euler solver for low-fidelity data whereas a relatively finer grid is utilized for high-fidelity data to obtain viscous solutions using the Spallart-Allmaras turbulence model. The performance metrics to compare the methods are determined as the test accuracy, physical training time, and the size of the high-fidelity samples. Results demonstrate that the proposed multi-fidelity neural network architectures outperform the multi-fidelity deep neural networks in predictive modeling using high dimensional inputs by improving the multi-fidelity prediction accuracy up to 78.7%.
Original language | English |
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Title of host publication | AIAA AVIATION 2022 Forum |
Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
ISBN (Print) | 9781624106354 |
DOIs | |
Publication status | Published - 2022 |
Event | AIAA AVIATION 2022 Forum - Chicago, United States Duration: 27 Jun 2022 → 1 Jul 2022 |
Publication series
Name | AIAA AVIATION 2022 Forum |
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Conference
Conference | AIAA AVIATION 2022 Forum |
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Country/Territory | United States |
City | Chicago |
Period | 27/06/22 → 1/07/22 |
Bibliographical note
Publisher Copyright:© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
Funding
The authors would like to express their gratitude to General Electric Gas Power, UK, for the research grant titled "Development of Convolutional Neural Network Based Predictive Modeling Code". The authors would also like to acknowledge TUBITAK for the research grant provided under the 218M471 TUBITAK 1001 project titled "Development of Multi-fidelity and Multidisciplinary Methodologies Integrating Sonic Boom, Aeroelasticity and Propulsion System for Supersonic Aircraft Design".