Abstract
A strip method has been developed for the prediction of subcritical damping characteristics for guidance of subsonic wind tunnel and flight flutter tests. The transient aerodynamic coefficients are found from a Fourier transform of the two-dimensional incompressible oscillatory coefficients. A series of transient aerodynamic influence coefficients (AIC's) has been derived including a newly denned matrix of aerodynamic lag AIC's. Compressibility, sweep and finite span effects are included by varying the lift curve slope and aerodynamic center locations on each strip in accord with static wind tunnel data. A collocation formulation of the subcritical flutter eigenvalue problem is presented. A special technique for solving the complex eigenvalue problem is reviewed and illustrated in an example of a restrained (cantilevered) wing with five strips and ten elastic degrees of freedom. Finally, the simplifications that result from reducing the size of the eigenvalue problem by modal methods are discussed.
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 callDisclaimer: 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.
