PSI - Issue 54

Wojciech Skarka et al. / Procedia Structural Integrity 54 (2024) 498–505 Bartosz Rodak/ Structural Integrity Procedia 00 (2019) 000 – 000

501

4

0 2

Y X Y X Y X Y

0

0

40mm

43,7mm 11,8mm 140,5mm 3,7mm 194,2mm 0 2,3mm

2 3 3 4 4 Edge round

13mm 130mm 4mm 200mm 0 1mm

The new geometry achieved an aerodynamic drag of 0.0617N. Which is a drop of 9.39% from the initial model. The following will show the differences between the input and output models. Comparing the input geometry to the output geometry, it can be seen in Figure 3 that the output geometry has a much slimmer profile and more rounding of the leading edge. Also in Table 2 above, it can be seen that node number two is positioned closer to the axis of symmetry and shifted more towards the trailing edge making the connecting element slimmer and therefore more aerodynamic. As for the pressure distribution in the symmetry axis, Figure 4a shows what effect the rounding of the leading edge has on the pressure generated in front of the connecting element. Analyzing the turbulent flows in Figure 4b, it can be seen that due to the more slender silhouette and the rounding of the leading edge, turbulence was significantly reduced at the nacelle-wing connecting surface.

Fig. 3. - Input to output geometry comparison (from top: input, output)

Fig. 4. (a) Comparison of pressure distribution on the element and on the plane of symmetry (from the top: initial, optimized); (b) comparison of visualization of turbulent flows on the coupling surface (from the top: initial, optimized)