**5. Conclusions**

The flutter phenomenon of AGARD 445.6 wing was determined by (a) a modal approach for a structural response; (b) an aerodynamic damping coefficient to predict the appearance of flutter phenomenon; (c) a strongly coupled FSI method to predict the aeroelastic response for subsonic and transonic flutter characteristics; (d) an experiment method to predict the aeroelastic response for subsonic flutter characteristics with wing structure; (e) and an IBM method to improve the interface between the fluid and solid of aircraft wing.

xc center of gravity θ<sup>p</sup> rotation of wing mp mass of wing

δ<sup>h</sup> 3D delta function

υ kinematic viscosity

Cp coefficient of pressure

G shear stress ρ density

α attack angle

**Author details**

**75**

Hoang Thi Kim Dung<sup>1</sup>

Technology, Hanoi, Vietnam

provided the original work is properly cited.

Ip inertial moment of wing

X coordinate of Eulerian point

x*<sup>l</sup>* coordinate of Lagrangian point

*DOI: http://dx.doi.org/10.5772/intechopen.91748*

F force that created by fluid go pass through the wing T moment that created by fluid go pass through the wing

*Research on Aeroelasticity Phenomenon in Aeronautical Engineering*

ΔU*<sup>l</sup>* volume of effect corresponded to Lagrangian point *l*

\* and Nguyen Phu Khanh<sup>2</sup>

1 School of Transportation Engineering, Hanoi University of Science and

\*Address all correspondence to: dung.hoangthikim@hust.edu.vn

2 Faculty of Vehicle and Energy Engineering, Phenikaa University, Hanoi, Vietnam

© 2020 The Author(s). Licensee IntechOpen. This chapter is distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/ by/3.0), which permits unrestricted use, distribution, and reproduction in any medium,

N set of Lagrangian points round Eulerian point *l*

αγζ coefficient of step Runge-Kutta calculation

E11 normal stress following x-coordinates E22 normal stress following y-coordinates E33 normal stress following z-coordinates

In brief, the major results could be summarized as follows:


For further research of aeroelasticity in the future, both experimental and numerical researches at low and high speed should be performed.
