Implementation of Multidisciplinary Multifidelity Uncertainty Quantification Methods in Sonic Boom Prediction

Hüseyin Emre Tekaslan, Şıhmehmet Yıldız, Yusuf Demiroğlu, Melike Nikbay

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

1 Citation (Scopus)

Abstract

In this paper, surrogate based approaches for multifidelity uncertainty quantification are implemented in a sonic boom prediction framework for improving the supersonic aircraft design process under uncertainties. The sonic boom prediction framework requires output from multidisciplinary analyses such as obtaining the flow field pressure distribution solution from a flow solver to generate the near-field pressure signature of the aircraft and then propagating this near-field pressure signature throughout the atmosphere to the ground by using aeroacoustic methods. The open-source SU2 suite is employed as a high fidelity flow analysis tool to obtain the aerodynamic solution while in-house post-processing scripts are developed to generate the necessary near-field pressure signature. For low-fidelity flow analysis, A502 PANAIR, a higher-order panel code to solve flows around slender bodies in low angles of attack for subsonic and supersonic regimes, is used. For nonlinear aeroacoustic propagation, NASA Langley Research Center code sBOOM is incorporated with the near-field pressure signature for enabling both high-fidelity and low-fidelity sonic boom calculations. Efficient uncertainty quantification tools are developed in-house by implementing multifidelity polynomial chaos expansion and multifidelity Monte Carlo methods. Several atmospheric parameters are considered to comprise randomness and these uncertainties are propagated into the sonic boom loudness prediction of a low boom aircraft called the JAXA wing-body. Finally, an assessment of multifidelity uncertainty quantification methods is presented in terms of their performances and numerical accuracies.

Original languageEnglish
Title of host publicationAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624106101
DOIs
Publication statusPublished - 2021
EventAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021 - Virtual, Online
Duration: 2 Aug 20216 Aug 2021

Publication series

NameAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021

Conference

ConferenceAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
CityVirtual, Online
Period2/08/216/08/21

Bibliographical note

Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.

Funding

All authors would like to express their gratitude to TUBITAK for the research grant provided under the 218M471 TUBITAK 1001 project titled as "Development of Multifidelity and Multidisciplinary Methodologies Integrating Sonic Boom, Aeroelasticity and Propulsion System for Supersonic Aircraft Design". Second and last authors would like to acknowledge the graduate thesis support provided by Istanbul Technical University Scientific Research Program for MYL-2019-42352 project titled as "Application of Multidisciplinary and Multifidelity Optimization Techniques for Supersonic Aircraft". Last author would like to thank NASA Langley Research Center for distributing sBOOM sonic boom prediction code internationally for academic research. Second and last authors would like to acknowledge the graduate thesis support provided by Istanbul Technical University Scientific Research Program for MYL-2019-42352 project titled as "Application of Multidisciplinary and Multifidelity Optimization Techniques for Supersonic Aircraft".

FundersFunder number
Langley Research Center
Istanbul Teknik ÜniversitesiMYL-2019-42352

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