Flutter phenomenon is a dynamic instability problem which may damage the aircraft structure in flight. Many mathematical models are applied to estimate the flutter speed of flight vehicles. In this study, the differential transformation method (DTM) is employed to analyze the dynamic stability of an aircraft wing in a subsonic regime. The wing is considered to be a cantilevered Euler-Bernoulli beam. The governing equations and boundary conditions which are solved by DTM are derived through the Hamilton’s principle. Goland wing and a High Altitude Long Endurance (HALE) wing are chosen as validation studies. The numerical results are obtained via a script written in MATHEMATICA tool and then compared with the exact solutions of the original Goland and HALE wings. In this work, flutter speed and frequency of the Goland wing are found as  and  and compared with the exact value in literature which are  and  [1]. Additionally, the flutter speed and frequency of the HALE wing are obtained as  and  and compared with the exact value in literature which are  and  [2]. Obtained results are in good agreement with the existing data in literature which shows that the implemented methodology in this study is applicable to such aeroelasticity problems. This investigation shows that the precision of the DTM is very high and it is a powerful tool for the flutter analysis of an aircraft wing.

REFERENCES

[1]      Lin, J. And Lliff, K.W., Aerodynamic Lift and Moment Calculations Using A closed Form Solution of The Possio Equation, NASA, 2000.

[2]      Patil, M. J., Hodges, D. H., & S. Cesnik, C. E. (2001). Nonlinear aeroelasticity and flight dynamics of high-altitude long-endurance aircraft. Journal of Aircraft, 38(1), 88-94.