Quick and Effective Modal and Flutter Analyses for Low Aspect Ratio Wings

الموضوعات :

Masoud Basiri ¹ , Hamid Farrokhfal ² , Masoud Mosayebi ³ , Reza Koohi ⁴

1 - Department of Mechanical Engineering, Malek-Ashtar University of Technology, Shahinshahr, Iran
2 - Department of Mechanical Engineering, Malek-Ashtar University of Technology, Shahinshahr, Iran
3 - Department of Mechanical Engineering, Malek-Ashtar University of Technology, Shahinshahr, Iran
4 - Department of Mechanical Engineering, Khomeinishahr Branch, Islamic Azad University, Khomeinishahr, Iran

تاريخ الإرسال : 23 الإثنين , شوال, 1441 تاريخ التأكيد : 18 السبت , ذو الحجة, 1441 تاريخ الإصدار : 16 الثلاثاء , ربيع الثاني, 1442

الکلمات المفتاحية: Flutter, Low Aspect Ratio, Unsteady Aerodynamics, Doublet Point Method, Equivalent Plate Model,

ملخص المقالة :

In the present work, an analytical study is proposed to investigate the flutter behavior of low-aspect-ratio wings in subsonic flow. An equivalent plate model is used for structural modelling of a semi-monocoque main wing, consisting of ribs, skins, and spars. Legendre polynomials are used in the Rayleigh-Ritz method as trial functions, and the first-order shear deformation theory is utilized to formulate the structural deformation. Boundary conditions are enforced by applying proper artificial springs. A doublet point method is used to calculate the unsteady aerodynamic loads. Chordwise pressure coefficient distribution at the tip and root of a rectangular wing oscillating in pitching motion is calculated. Flutter analysis is performed using the k method. Instead of using the computationally expensive finite element method, the proposed approach is intended to achieve purposes of quick modelling and effective analysis in free vibration and flutter analyses of low-aspect-ratio wings for preliminary design applications. The effects of aspect ratio on the flutter behavior of wings in subsonic flow are investigated. The obtained results are validated with the results available in the literature.

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