Evaluation of Cross-Section and Wing Length in Free Vibration Analysis of Aircraft Wings

Yıl 2020, Cilt: 4 Sayı: 2, 17 - 24, 28.12.2020

Savaş Evran , Mustafa Kurt , Arzu Kurt

https://doi.org/10.30518/jav.778273

Cited By: 2

Öz

This study presents the numerical free vibration analysis of aircraft wings created using different airfoil cross sections such as NACA 0009, NACA 2424, and NACA 4415. Aircraft wings were made of different lengths. Numerical frequency analyses were conducted Taguchi L9 orthogonal array with two control factors including three levels and so nine numerical modal analyses were performed. Airfoil cross sections and lengths of aircraft wings were used as the first and the second control factors. To detect the control factors with optimal levels, analysis of signal-to-noise (S/N) ratio was employed. In addition, analysis of variance (ANOVA) at the 95 % confidence level was implemented to carry out percent contributions of airfoil cross sections and lengths of aircraft wings on free vibration. As can be summarized from this study, the maximum free vibration behavior was obtained using aircraft wings profiled NACA 2424 wing lengths with 5 in meter. Also, the most dominant control factors were found to be airfoil type with 85.21 % effect and wing length with 12.87 % effect, according to ANOVA.

Anahtar Kelimeler

Airfoil, Free vibration, ANSYS, Taguchi method

Destekleyen Kurum

Çanakkale 18 Mart Üniversitesi

Proje Numarası

3313

Teşekkür

The research described in this paper was financially supported by the Research Fund of the Canakkale Onsekiz Mart University. Project Number: 3313

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