Somayye Siahat-Nosrati, Sana Mandouzei, Saeed Hosseini
DOI Number: N/A
Conference number: HiSST-2025-142
This research presents the development of a methodology for conceptual multidisciplinary design and optimization of supersonic civil aircraft, and the developed process is implemented within an automated aircraft design framework. The framework integrates low-fidelity and high-fidelity methods to address the unique challenges of supersonic transport, including aerodynamics, , propulsion, performance, and weight. Key features of the framework include a parametric geometry modeling tool, a surrogate optimization methodology, and a modular architecture for integrating multiple disciplines. A case study is conducted for the design of a Mach 1.6, 72-passenger aircraft with a range of 7,000 km. The aircraft configuration is developed using rapid engineering methods, area ruling requirements, and a modular optimization process. The subsonic emission analysis methodology is supplemented with methods for the estimation of emissions at supersonic speed. The results demonstrate the feasibility of the proposed design, with detailed aircraft characteristics and dimensions provided. Future work will focus on incorporating high-fidelity structural weight estimation, supersonic emission analysis, and sonic boom
constraints to further enhance the framework’s capabilities.