The flutter behavior of a thin panel resting on a linear elastic foundation is studied, using an analogy with the flutter of a panel of the same geometry without spring support. With quasi-steady aerodynamic loading, it is observed that there is a change not only in the flutter frequency, but also in the total damping of the system, due to the elastic foundation. Furthermore, it is found that for small values of aerodynamic damping and spring stiffness, the quasi-static approach is reasonable, whereas for high values of aerodynamic damping or of spring stiffness, quasi-static theory is inadequate. For high values of spring stiffness, the flutter mode of the panel exhibits traveling wave motion
Panel flutter is an aeroelastic phenomenon that can cause failure of panels of wings, fuselages and ...
Experimental studies of panel flutter using thin metal plates were conducted at a Mach number of 1.3...
The supersonic flutter of wide panels on discrete flexible supports is investigated for three differ...
The flutter behavior of a thin panel resting on a linear elastic foundation is studied, using an ana...
The present study examines the problem of flutter of flat rectangular panels subjected to static inp...
This report presents investigations on the problem of flutter of initially stressed rectangular pane...
The effect of various parameters on the flutter of elliptic panels is studied by simple theoretical...
Experimental studies of panel flutter using thin metal plates were conducted at a Mach number of 1.3...
"Representative experimental results are presented to show the current status of the panel flutter p...
Experimental studies of panel flutter were conducted at a Mach num-ber of 1.3 to verify the existenc...
The flutter of two-bay clamped-edge and simply supported panels at supersonic Mach numbers is studie...
Flutter of flat rectangular panels based on three-dimensional supersonic potential flo
A Rayleigh type analysis involving chosen modes of the panel as degrees of freedom is used to treat ...
Flutter characteristics for yaw angles between 15 deg and 90 deg were determined experimentally for ...
An aeroelastic model based on a two-dimensional unsteady vortex-lattice method is used to study the ...
Panel flutter is an aeroelastic phenomenon that can cause failure of panels of wings, fuselages and ...
Experimental studies of panel flutter using thin metal plates were conducted at a Mach number of 1.3...
The supersonic flutter of wide panels on discrete flexible supports is investigated for three differ...
The flutter behavior of a thin panel resting on a linear elastic foundation is studied, using an ana...
The present study examines the problem of flutter of flat rectangular panels subjected to static inp...
This report presents investigations on the problem of flutter of initially stressed rectangular pane...
The effect of various parameters on the flutter of elliptic panels is studied by simple theoretical...
Experimental studies of panel flutter using thin metal plates were conducted at a Mach number of 1.3...
"Representative experimental results are presented to show the current status of the panel flutter p...
Experimental studies of panel flutter were conducted at a Mach num-ber of 1.3 to verify the existenc...
The flutter of two-bay clamped-edge and simply supported panels at supersonic Mach numbers is studie...
Flutter of flat rectangular panels based on three-dimensional supersonic potential flo
A Rayleigh type analysis involving chosen modes of the panel as degrees of freedom is used to treat ...
Flutter characteristics for yaw angles between 15 deg and 90 deg were determined experimentally for ...
An aeroelastic model based on a two-dimensional unsteady vortex-lattice method is used to study the ...
Panel flutter is an aeroelastic phenomenon that can cause failure of panels of wings, fuselages and ...
Experimental studies of panel flutter using thin metal plates were conducted at a Mach number of 1.3...
The supersonic flutter of wide panels on discrete flexible supports is investigated for three differ...