抄録
This paper presents the verification and application of the flutter
analysis framework using fluid-structure interaction simulation
(FSI). This approach is verified by consulting semi-analytical
reference solutions from LINSUB. Aeroelastic eigenmodes and
mode shapes obtained by FSI are compared; the proposed approach
is found to be capable of accurately obtaining flutter characteristics,
even under the presence of aerodynamic coupling between structural
modes. This verified approach is applied for predicting the
flutter boundary of part-speed transonic stall flutter, which is experienced
during the rig test. The flutter boundary obtained by FSI
simulations agrees well in a qualitative sense for the high speed
lines. However, the simulations cannot reproduce the end of the
flutter boundary for the low speed lines. The reason for the mismatch
in the flutter boundary is discussed, and it is concluded that
highly complex and sensitive near-wall flow phenomena are related
to the shock position and flutter characteristics.
