Hypersonic inlet flow field reconstruction dominated by shock wave and boundary layer based on small sample physics-informed neural networks-Reference-Cited by-同舟云学术

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Hypersonic inlet flow field reconstruction dominated by shock wave and boundary layer based on small sample physics-informed neural networks

Published:2024-07 Issue: Volume:150 Page:109205
ISSN:1270-9638
Container-title:Aerospace Science and Technology
language:en
Short-container-title:Aerospace Science and Technology

Author:

Guo Mingming,Deng Xue,Ma Yue,Tian Ye^ORCID,Le Jialing,Zhang Hua

Publisher

Elsevier BV

Reference33 articles.

1. Dual-mode operation and transition in axisymmetric scramjets;Liu;AIAA J,2019

2. Design optimization and off-design performance analysis of axisymmetric scramjet intakes for ascent flight;Brahmachary;Phys. Fluids,2022

3. Numerical investigation of axisymmetric intake flowfield and performance for scramjet-powered ascent flight;Fujio;Aerosp. Sci. Technol.,2023

4. Experimental investigations of the hypersonic stream-traced performance inlet at subdesign Mach number;Johnson;AIAA J,2023

5. Investigation of shock dynamics in an axisymmetric Inlet/Isolator with attached boundary layers;Leonard;J. Fluid Mech.,2020

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