Al

0.2 0.4 0.6 0.8 q° Figure 3.3 Relative change in lift caused by aeroelastic effect.

encountered. Moreover, the structure will not tolerate infinite deformation, and failure will take place at some finite value of 0.

When the system parameters are within the bounds of validity for linear theory, another fascinating feature of this problem emerges. One can invert the expression for 6 to obtain iE.ll. «r \q

0 0

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