Abstract:

Three methods to calculate the divergence dynamic pressure of static aeroelasticity are introduced, i.e . the flexibility method, the mode method and the flutter method, and the consistence of the three methods is proved. The divergence speeds of five plate wings are calculated by the three methods. Their true divergence speeds are obtained from a low speed wind tunnel test. The calculated results are compared with the experiment results, and the consistence is validated. Besides, the principle to select the number of structure modes based on the divergence eigenvector in the mode method and the flutter method is produced.

Key words: aeroelasticity, static aeroelasticity, divergence, composite wing, forward sweep wing, wind tunnel test