A modern course in aeroelasticity by Earl H. Dowell, Howard C. Curtiss Jr. (auth.), Earl H.

By Earl H. Dowell, Howard C. Curtiss Jr. (auth.), Earl H. Dowell, Howard C. Curtiss Jr., Robert H. Scanlan, Fernando Sisto (eds.)

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Extra resources for A modern course in aeroelasticity

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The determination of such eigenfunctions may itself be fairly complicated, however. An alternative procedure can be employed which expands the solution for the variable property wing in terms of the eigenfunctions of the constant property wing. This is the last of the reasons previously cited for examining the eigenfunctions. 1). 24) * For a more detailed mathematical discussion of the above, see Hildebrand [6], pp. 224-234. This problem is one of a type known as 'Sturm-Liouville Problems'. 25) where GJ (GJ)ref 'Y=-- Let as before.

8) Note that Ä 2 is a nondimensional ratio of aerodynamic to elastic stiffness; we shall call it and similar numbers we shall encounter an 'aeroelastic stiffness number'. It is as basic to aeroelasticity as Mach number and Reynolds number are to fluid mechanics. 16 Fluid flow over a flexible wall. as weil as in the (uniform) beam-rod wing model, iJCL q(lc)eiJa GI (Low speed) fluid flow over a flexible wall A mathematically similar problem arises when a flexible plate is embedded in an otherwise rigid surface.

13 Roll rate vs dynamic press ure. 14 Roll rate vs dynamic pressure. then 'rolling reversal' is said to have occurred and the corresponding q = qR is called the 'reversal dynamic pressure'. The basic phenomenon is the same as that encountered previously as 'control surface reversal'. 5a,b. It is worth emphasizing that the divergence condition obtained above by permitting p to be determined by (static) rolling equilibrium will be different from that obtained previously by assuming p = O. The latter physically corresponds to an aircraft constrained not to roll, as might be the case for some wind tunnel models.

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