Abstract
A computational program using a CFD-CSD coupled method has been developed to study the problem of low supersonic curved panel flutter. So far the supersonic aerodynamic model has been commonly employed to compute flutter boundaries. However, the present CFD-CSD coupled method makes it possible to analyze flutter boundaries at all speeds including transonic speeds. The computed flutter dynamic pressure for M∞=3 agrees with others’ results. A curved panel flutter were analyzed at a low supersonic speed, M∞=1.2. The flutter for small curvature panels is first-mode flutter, which is similar to flat panel flutter, whereas it becomes higher-mode flutter for larger curvature plates. In this study, flutter boundaries for an access panel have also been simulated. Its critical dynamic pressure becomes significantly lower compared with the case of a panel with its all edges simply supported.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callMore From: JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
