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This paper presents an advanced natural laminar flow (NLF) design method for supersonic and transonic wings, integrating a modular approach that combines various flow solvers and stability analysis techniques. It discusses the effects of stability analysis options and introduces new methods for controlling transition mechanisms, including a modification for independent control of Tollmien-Schlichting and cross flow modes. The findings aim to enhance the efficiency and accuracy of NLF design, expanding its a

Author

trongnghia13092018

Language

EN