Free vibration analysis of composite aircraft wings modeled as thin-walled beams with NACA airfoil sections

Eken, Seher

doi:10.1016/j.tws.2019.01.042

Cited by 25 publications

(10 citation statements)

References 23 publications

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“…In this section, the presented crack detection method is applied to a thin-walled wing with NACA0015 cross section. The thickness distribution of the NACA0015 airfoils are given by the following equation (Eken, 2019)where truex¯=x/Chord and x is distance from the leading edge of the airfoil varying between 0 and Chord. Material properties are the same with the solid wing, and geometrical properties of the thin-walled wing with front and rear spars are listed in Table 8.…”

Section: Numerical Examplesmentioning

confidence: 99%

“…Investigating the vibration of wings as an airfoil cross-section beam may lead to some challenges such as calculating the torsional constant, stress intensity factor, shear centre location and shear stress. Some researchers studied the free vibration analysis of composite straight wings with a Natinal Advisory Committee for Aeronautics (NACA) airfoil sections (Eken, 2019; Hwu and Gai, 2003).…”

Section: Introductionmentioning

confidence: 99%

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Multi-crack detection in general cross-section swept wings based on natural frequency changes

Barzegar

Mohebpour

Alighanbari

2020

Journal of Vibration and Control

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In this article, a multi-crack detection method, which is based on natural frequency changes and the concept of modal strain energy, is for the first time developed for the general cross-section swept tapered wings under coupled bending-torsional vibration and applied to the solid and thin-walled airfoil cross-section wings. The presented method is able to handle the problems with an unknown number of cracks and predicts the number of existent cracks, their locations and depths by optimization of an appropriate objective function. The stress intensity factors of airfoil-shaped crack surfaces are obtained using an approximation method. Inputs of the detection method are natural frequencies of uncracked and cracked wings which are calculated by using a mathematical model and finite element method software ANSYS, respectively, and validated by comparison with former research studies. In the mathematical model, the Rayleigh–Ritz method is used to calculate the coupled bending-torsional mode shapes of the uncracked wing and their corresponding natural frequencies. Results demonstrate that the proposed method has precisely predicted the number, locations and depths of cracks in all case studies.

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Section: Numerical Examplesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Multi-crack detection in general cross-section swept wings based on natural frequency changes

Barzegar

Mohebpour

Alighanbari

2020

Journal of Vibration and Control

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“…The location at 0.3 to 0.6 of the airfoil chord length is the most effective slot locations for applying suction and stall angle is increased from 10 °to 16 °by applying slot modification. Flutter is an important phenomenon and affect aeroelastic stability which includes aerodynamic, elastic and inertial forces and Eken [19] uses thin walled composite beam theory to investigate three different NACA 4-digit-series (NACA 0009, NACA 0015, NACA 0021). The lowest frequency is found at NACA 0021 and the highest is found at NACA 0009 wing.…”

Section: Introductionmentioning

confidence: 99%

Flow and Mechanical Characteristics of a Modified Naca Wing Geometry

Yavuz¹

2021

Çukurova Üniversitesi Mühendislik Fakültesi Dergisi

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The flying ability is directly related to the structure of the wing geometry. The wing structure is designed differently according to each working conditions. In this study, a free-formed airfoil section was designed and the behaviour of the model under the influence of flow was investigated in terms of diving and takeoff angles. Computational fluid dynamics method was used in the analysis. The sensitivity of the method was checked by comparing the solution of a NACA airfoil section with the experimental results in the literature and its usability in the study was accepted. Also, in the study, the wing geometry was modelled as 3D and layered, and its mechanical properties were examined. The designed airfoil has more dominant flow structure in the lift direction. Non-symmetrical airfoil causes unsymmetrical Cl-Cd distribution. As a result of the wing structure being more dominant in lift, it was observed that the deformation and stress results of the positive angle of attack were higher than the negative results. Depending on the angle of attack, the pressure and flow effects on the wing caused a higher bending-torsion effect and increased the stresses in the fixation region of the wing. The lowest deformation and average stresses occurred at -4°a ngle of attack. The results are discussed as a result of flow and mechanical findings.

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“…Bayraktar and Demirtaş [1] investigated the free vibration of a NACA 4415 airfoil profiled wing as a cantilever beam using theoretical and numerical methods for different modes. Eken [2] presented the model analysis of composite aircraft wings created in accordance with thin-walled beams which have NACA airfoil sections. Tenguria et al [3] analyzed the free vibration characteristic for blade of horizontal axis wind turbine and they also used NACA 634-221 model.…”

Section: Introductionmentioning

confidence: 99%

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

Evran

Kurt

2020

Journal of Aviation

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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 by using NACA 2424 wing profiles with a length of 5 meters. 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.

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Free vibration analysis of composite aircraft wings modeled as thin-walled beams with NACA airfoil sections

Cited by 25 publications

References 23 publications

Multi-crack detection in general cross-section swept wings based on natural frequency changes

Multi-crack detection in general cross-section swept wings based on natural frequency changes

Flow and Mechanical Characteristics of a Modified Naca Wing Geometry

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

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