By Karl Popper, David Miller
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Extra info for A Pocket Popper
11) is valid only when q/qD 1; and it cannot predict divergence. 3. 8). Hence, aeroelasticity can also be thought of as the study of aerodynamic + elastic feedback systems. † Having exhausted the interpretations of this problem, we will quickly pass on to some slightly more complicated problems, but whose physical content is similar. 4. For simplicity, we take α0 = CMAC0 = 0; hence, α = αe. 12) the reader with some knowledge of feedback theory as in, for example, Savant and Gere . 4. Typical section with control surface.
Typical section with control surface. 14) where SH is the area of control surface, cH the chord of the control surface and CH the (nondimensional) aerodynamic hinge moment coef∂CL ∂CM AC ∂CH ∂CH L ﬁcient. As before, ∂C ∂α , ∂δ , ∂δ , ∂α , ∂δ are aerodynamic conH stants which vary with Mach and airfoil geometry. Note ∂C ∂δ is typically negative. The basic purpose of a control surface is to change the lift (or moment) on the main lifting surface. It is interesting to examine aeroelastic eﬀects on this lift.
Presumably structural failure would occur for q > qD, even though αe∞ is ﬁnite. It would be most interesting to try to achieve the above equilibrium diagram experimentally. The above discussion does not exhaust the possible types of nonlinear behavior for the typical section model. 2. One Dimensional Aeroelastic Model of Airfoils Beam-rod representation of large aspect ratio wing † We shall now turn to a more sophisticated, but more realistic beam-rod model which contains the same basic physical ingredients as the typical section.