**4.3 Results**

The results of IBM method were analyzed at three different instants (**Figure 16**):


The wing deformation was maximum at the tip of the wing and decreased gradually into the root of the wing over time. However, the normal stress was found to have an opposite tendency in comparison with deformation. The maximum normal stress was observed at the root of the wing, while the minimum normal stress was found at the tip of the wing (**Figures 17** and **18**). It could be explained by the fixed support with fuselage at the root of the wing and free support at the tip of the wing [13]. These remarks were in well agreement with the experimental results within a relative error less than 10% (**Table 7**).

**Figure 17.** *Instant normal stress—Rectangular wing.*
