Application Of Cfd To Sonic Boom Near And Mid Flow Field Prediction

Author : Mathias Wintzer
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (89 download)

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Download or read book Optimization and Adjoint-based CFD for the Conceptual Design of Low Sonic Boom Aircraft written by Mathias Wintzer and published by . This book was released on 2012 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: For future civil supersonic aircraft to have the operational flexibility offered by current subsonic aircraft, some means of reducing their sonic boom to acceptable levels is required. An effective technique by which the sonic boom ground signal may be altered, and potentially minimized, is through careful shaping of external features of the aircraft. By considering the detailed aircraft shape using nonlinear flow solvers, accurate assessments of sonic boom can be made during multi-disciplinary conceptual design optimization. Such capability would enable the development of aircraft satisfying not only a requirement on low boom, but also on the range of constraints and mission goals necessary to produce a viable aircraft design. This work presents a multi-level framework for the conceptual design of low sonic boom aircraft. The development of a robust, automated tool using output-driven mesh adaptation enables accurate prediction of sonic boom. Results are validated with available experimental data for a variety of signal forms. An approach combining linear supersonic potential theory with atmospheric propagation and loudness prediction methods is used to generate low-boom near-field signals subject to lift and equivalent area constraints. This signal generator is then used to build a response surface fit that enables a conceptual-level design optimization to develop aircraft configurations with low boom. The imposition of a diverse range of multi-disciplinary design constraints ensures a viable aircraft. Once a satisfactory baseline is obtained, the design is transferred to the CFD domain, where an adjoint-driven inverse design approach is used to determine the detailed aircraft shape. This optimization seeks to match the near-field pressure target associated with the conceptual baseline design, subject to geometric constraints that ensure conceptual-level performance predictions are preserved. An aircraft design example is presented, demonstrating the application of this approach on a supersonic business jet.