Abstract
In this paper, we present the results of a numerical study of wind tunnel wall effects on the flutter characteristics of an airplane model. The airplane model corresponds to a twin engine airplane flying in the transonic range. The wind tunnel chosen is the Transonic Dynamic Tunnel (TDT) located at NASALangley Research Center. It is shown that while the slotted wind tunnel walls in the TDT have a relatively minor influence on the steady aerodynamics, their effects on the unsteady aerodynamics could be substantial. It is therefore important to take the wall effects into account, especially when the flutter frequencies are expected to lie in the same range as the tunnel acoustic natural frequencies.
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