Araştırma Makalesi
BibTex RIS Kaynak Göster

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

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.

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

Kaynakça

  • [1] M. Bayraktar and A. Demirtaş, "Free vibration analysis of an aircraft wing by considering as a cantilever beam," Selcuk University Journal of Engineering, Science and Technology, 7, 12-21, 2019.
  • [2] S. Eken, "Free vibration analysis of composite aircraft wings modeled as thin-walled beams with NACA airfoil sections," Thin-Walled Structures, 139, 362-371, 2019.
  • [3] N. Tenguria, N. Mittal and S. Ahmed, "Modal analysis for blade of horizontal axis wind turbine," Asian Journal of Scientific Research, 4, 326-334, 2011.
  • [4] H.A. Alabaş, M. Albatran, T. Çelik, M. Lüleci and Ü.D. Göker, "Oyuk boşluk yapısının kanat profili üzerine etkisi," Journal of Aviation, 3, 89-105, 2019.
  • [5] M. Bakirci, H. Ceylan and S. Yilmaz, "NACA 23012 ve NREL S 809 kanat kesitlerinin HAD ile analizi," EJOVOC Electronic Journal of Vocational Colleges, 5, 52-61, 2015.
  • [6] M. Doğru, I. Göv and Ü. Korkmaz, "Uçuş Esnasında değiştirilebilir kanat profili kullanarak NACA 4412’nin aerodinamik performansının artırılması," Gazi Üniversitesi Mühendislik-Mimarlık Fakültesi Dergisi, 34:2, 1109-1125, 2019.
  • [7] R.I. Rubel, M.K. Uddin, M.Z. Islam and M. Rokunuzzaman, "Numerical and experimental investigation of aerodynamics characteristics of NACA 0015 aerofoil," International Journal of Engineering Technologies, 2, 132-141, 2016.
  • [8] T. Durhasan, "NACA 0015 kanat profilinin etrafındaki akışın firar kenarından akış emme ile kontrol edilmesi," Bilecik Şeyh Edebali Üniversitesi Fen Bilimleri Dergisi, 6, 153-160, 2019.
  • [9] T. Oktay and Ö.Ö. Kanat, "Aerodynamic effects of designing a suction channel over NACA 4412 wing," Avrupa Bilim ve Teknoloji Dergisi, 17, 1001-1007, 2019.
  • [10] S. Evran, "Natural frequency analysis of layered functionally graded beams," Anadolu University of Sciences & Technology-A: Applied Sciences & Engineering, 19, 83-94, 2018.
  • [11] S. Evran and Y. Yilmaz, "The effects of layer arrangements on fundamental frequency of layered beams in axial direction," Sakarya Üniversitesi Fen Bilimleri Enstitüsü Dergisi, 21, 968-977, 2017.
  • [12] S. Evran, "Numerical First Mode Frequency Analysis of Axially Layered Functionally Graded Tapered Beams," Niğde Ömer Halisdemir Üniversitesi Mühendislik Bilimleri Dergisi, 7, 399-406, 2018.
  • [13] S. Evran, "Three-dimensional modal analysis of beams with triangular and hexagonal cross sections using different ceramic materials," International Journal of Engineering and Innovative Research, 2, 129-136, 2020.
  • [14] Y. Yilmaz and S. Evran, "Free vibration analysis of axially layered functionally graded short beams using experimental and finite element methods," Science and Engineering of Composite Materials, 23, 453-460, 2016.
  • [15] H.-S. Shen, Functionally graded materials: nonlinear analysis of plates and shells, Boca Raton, New York, London, CRC Press, 2009.
  • [16] M. Talha and B.N. Singh, "Static response and free vibration analysis of FGM plates using higher order shear deformation theory," Applied Mathematical Modelling, 34, 3991-4011, 2010.
  • [17] "Airfoiltools" http://www.airfoiltools.com. [ Date of access: 27-June-2020]
  • [18] P.J. Ross, Taguchi techniques for quality engineering, 2nd Edition, New York, USA, McGraw-Hill International Editions, 1996.
  • [19] ANSYS Help, Version 13. (ANSYS Inc, Canonsburg, PA, USA)

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

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.

Proje Numarası

3313

Kaynakça

  • [1] M. Bayraktar and A. Demirtaş, "Free vibration analysis of an aircraft wing by considering as a cantilever beam," Selcuk University Journal of Engineering, Science and Technology, 7, 12-21, 2019.
  • [2] S. Eken, "Free vibration analysis of composite aircraft wings modeled as thin-walled beams with NACA airfoil sections," Thin-Walled Structures, 139, 362-371, 2019.
  • [3] N. Tenguria, N. Mittal and S. Ahmed, "Modal analysis for blade of horizontal axis wind turbine," Asian Journal of Scientific Research, 4, 326-334, 2011.
  • [4] H.A. Alabaş, M. Albatran, T. Çelik, M. Lüleci and Ü.D. Göker, "Oyuk boşluk yapısının kanat profili üzerine etkisi," Journal of Aviation, 3, 89-105, 2019.
  • [5] M. Bakirci, H. Ceylan and S. Yilmaz, "NACA 23012 ve NREL S 809 kanat kesitlerinin HAD ile analizi," EJOVOC Electronic Journal of Vocational Colleges, 5, 52-61, 2015.
  • [6] M. Doğru, I. Göv and Ü. Korkmaz, "Uçuş Esnasında değiştirilebilir kanat profili kullanarak NACA 4412’nin aerodinamik performansının artırılması," Gazi Üniversitesi Mühendislik-Mimarlık Fakültesi Dergisi, 34:2, 1109-1125, 2019.
  • [7] R.I. Rubel, M.K. Uddin, M.Z. Islam and M. Rokunuzzaman, "Numerical and experimental investigation of aerodynamics characteristics of NACA 0015 aerofoil," International Journal of Engineering Technologies, 2, 132-141, 2016.
  • [8] T. Durhasan, "NACA 0015 kanat profilinin etrafındaki akışın firar kenarından akış emme ile kontrol edilmesi," Bilecik Şeyh Edebali Üniversitesi Fen Bilimleri Dergisi, 6, 153-160, 2019.
  • [9] T. Oktay and Ö.Ö. Kanat, "Aerodynamic effects of designing a suction channel over NACA 4412 wing," Avrupa Bilim ve Teknoloji Dergisi, 17, 1001-1007, 2019.
  • [10] S. Evran, "Natural frequency analysis of layered functionally graded beams," Anadolu University of Sciences & Technology-A: Applied Sciences & Engineering, 19, 83-94, 2018.
  • [11] S. Evran and Y. Yilmaz, "The effects of layer arrangements on fundamental frequency of layered beams in axial direction," Sakarya Üniversitesi Fen Bilimleri Enstitüsü Dergisi, 21, 968-977, 2017.
  • [12] S. Evran, "Numerical First Mode Frequency Analysis of Axially Layered Functionally Graded Tapered Beams," Niğde Ömer Halisdemir Üniversitesi Mühendislik Bilimleri Dergisi, 7, 399-406, 2018.
  • [13] S. Evran, "Three-dimensional modal analysis of beams with triangular and hexagonal cross sections using different ceramic materials," International Journal of Engineering and Innovative Research, 2, 129-136, 2020.
  • [14] Y. Yilmaz and S. Evran, "Free vibration analysis of axially layered functionally graded short beams using experimental and finite element methods," Science and Engineering of Composite Materials, 23, 453-460, 2016.
  • [15] H.-S. Shen, Functionally graded materials: nonlinear analysis of plates and shells, Boca Raton, New York, London, CRC Press, 2009.
  • [16] M. Talha and B.N. Singh, "Static response and free vibration analysis of FGM plates using higher order shear deformation theory," Applied Mathematical Modelling, 34, 3991-4011, 2010.
  • [17] "Airfoiltools" http://www.airfoiltools.com. [ Date of access: 27-June-2020]
  • [18] P.J. Ross, Taguchi techniques for quality engineering, 2nd Edition, New York, USA, McGraw-Hill International Editions, 1996.
  • [19] ANSYS Help, Version 13. (ANSYS Inc, Canonsburg, PA, USA)
Toplam 19 adet kaynakça vardır.

Ayrıntılar

Birincil Dil İngilizce
Konular Uzay Mühendisliği
Bölüm Araştırma Makaleleri
Yazarlar

Savaş Evran 0000-0002-7512-5997

Mustafa Kurt 0000-0002-5021-992X

Arzu Kurt 0000-0003-3196-100X

Proje Numarası 3313
Yayımlanma Tarihi 28 Aralık 2020
Gönderilme Tarihi 8 Ağustos 2020
Kabul Tarihi 26 Eylül 2020
Yayımlandığı Sayı Yıl 2020 Cilt: 4 Sayı: 2

Kaynak Göster

APA Evran, S., Kurt, M., & Kurt, A. (2020). Evaluation of Cross-Section and Wing Length in Free Vibration Analysis of Aircraft Wings. Journal of Aviation, 4(2), 17-24. https://doi.org/10.30518/jav.778273

Journal of Aviation - JAV 


www.javsci.com - editor@javsci.com


9210This journal is licenced under a Creative Commons Attiribution-NonCommerical 4.0 İnternational Licence