Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed

Thi Tuyet Nhung Le; Chi-Cong Nguyen; Hoang Nam Vang

doi:doi:10.11648/j.ijmea.s.2015030103.16

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Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed

Thi Tuyet Nhung Le, Chi-Cong Nguyen, Hoang Nam Vang

Published in International Journal of Mechanical Engineering and Applications (Volume 3, Issue 1-3)

Received: 9 December 2014 Accepted: 26 December 2014 Published: 21 January 2015

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Abstract

The purpose of this study is to calculate the geometries parameters for a wing NACA0012 as well as its materials in order to observe the instability of aeroelasticity such as divergence and flutter phenomenon in the low speed wind tunnel (38 m/s). Approaches used are the theories of aeroelasticity for the static and dynamic instability problem of the wing. The 3D divergence problem is solved first by strip theory to preliminary design the non-tapper wing and the suitable material for static instability at low speed. The V – g method for flutter analysis is carried out to verify the dynamic instability speed designed. A wing with wing chord, wing length is obtained in accordance with the testing section of the considered wind tunnel, and the suitable material is PU. The preliminary design were carried out for the the divergence phenomenon and divergence speeds can be observed at 30.34 m/s [10]. This study continues with the results based on dimensionless analysis of wing’s parameters on flutter speed.

Published in	International Journal of Mechanical Engineering and Applications (Volume 3, Issue 1-3) This article belongs to the Special Issue Transportation Engineering Technology
DOI	10.11648/j.ijmea.s.2015030103.16
Page(s)	35-40
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2015. Published by Science Publishing Group

Keywords

Aeroelasticity, Bench Test for NACA0012, Flutter velocity, V – G Method

References

[1]	Guertin, Master thesis “The Applycation of Finite Element Method to Aeroelastic Lifting Surface Flutter” Rice University, April 2012
[2]	Theodorsen T., “General Theory of Aerodynamic Instability and the Mechanism of Flutter”, NACA Report 496, 1935.
[3]	Theodorsen T., Garrick, I. E., “Mechanism of Flutter A Theoretical and Experimental Investigation of the Flutter Problem”, NACA Report 685, 1940.
[4]	Ashley H., Zartarian G., “Piston Theory – A New Aerodynamic Tool for the Aeroelastician”, Twenty-Fourth Annual Meeting, IAS, New York, January 23-26, 1956.
[5]	Yates E. C., “Modified-Strip-Analysis Method for Predicting Wing Flutter at Subsonic to Hypersonic Speeds”, Journal of Aircraft Vol. 3, No. 1, 1966.
[6]	Steven L. Brunton., “Empirical State-Space Representations for Theodorsen’s Lift Model”, Princeton University, Princeton, April 17, 2012.
[7]	R. A. Frazer, W. J. Duncan, and A. R. Collar, “Elementary matrices and some applications to dynamics and differential equations”. Cambridge [Eng.] The University press, 1938.
[8]	E. H. Dowell, R. Clark, D. Cox, H. C. Curtiss, J. W. Edwards, K. C. Hall, D. A. Peters, R. H. Scanlan, E. Simiu, F. Sisto, and T. W. Strganac, “A modern course in Aeroelasticity”. Springer, 2004.
[9]	Smilg, В., and L. S. Wasserman, “Application of Three-Dimensional Flutter Theory to Aircraft Structures”, U.S. Army Air Force Tech. Rept. 4798, 1942.
[10]	T. A. Nguyen, H. N. Vang, Viet Khai Nguyen, Thi Tuyet Nhung LE, Chi-Cong Nguyen, “Design of aeroelasticity bench test for NACA0012 wing model in the low speed wind tunnel”, Journal for Research and Technology of HCM City University of Transport 7+8-9/2013, 163-169, 2013.
[11]	T. Theodorsen and I. E. Garrick, “Mechanism of flutter: a theoretical and experimental investigation of flutter problem”, NACA Report 685, 1938.

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APA Style

Thi Tuyet Nhung Le, Chi-Cong Nguyen, Hoang Nam Vang. (2015). Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed. International Journal of Mechanical Engineering and Applications, 3(1-3), 35-40. https://doi.org/10.11648/j.ijmea.s.2015030103.16

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ACS Style

Thi Tuyet Nhung Le; Chi-Cong Nguyen; Hoang Nam Vang. Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed. Int. J. Mech. Eng. Appl. 2015, 3(1-3), 35-40. doi: 10.11648/j.ijmea.s.2015030103.16

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AMA Style

Thi Tuyet Nhung Le, Chi-Cong Nguyen, Hoang Nam Vang. Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed. Int J Mech Eng Appl. 2015;3(1-3):35-40. doi: 10.11648/j.ijmea.s.2015030103.16

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@article{10.11648/j.ijmea.s.2015030103.16,
  author = {Thi Tuyet Nhung Le and Chi-Cong Nguyen and Hoang Nam Vang},
  title = {Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed},
  journal = {International Journal of Mechanical Engineering and Applications},
  volume = {3},
  number = {1-3},
  pages = {35-40},
  doi = {10.11648/j.ijmea.s.2015030103.16},
  url = {https://doi.org/10.11648/j.ijmea.s.2015030103.16},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijmea.s.2015030103.16},
  abstract = {The purpose of this study is to calculate the geometries parameters for a wing NACA0012 as well as its materials in order to observe the instability of aeroelasticity such as divergence and flutter phenomenon in the low speed wind tunnel (38 m/s). Approaches used are the theories of aeroelasticity for the static and dynamic instability problem of the wing. The 3D divergence problem is solved first by strip theory to preliminary design the non-tapper wing and the suitable material for static instability at low speed. The V – g method for flutter analysis is carried out to verify the dynamic instability speed designed. A wing with wing chord, wing length is obtained in accordance with the testing section of the considered wind tunnel, and the suitable material is PU. The preliminary design were carried out for the the divergence phenomenon and divergence speeds can be observed at 30.34 m/s [10]. This study continues with the results based on dimensionless analysis of wing’s parameters on flutter speed.},
 year = {2015}
}

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TY  - JOUR
T1  - Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed
AU  - Thi Tuyet Nhung Le
AU  - Chi-Cong Nguyen
AU  - Hoang Nam Vang
Y1  - 2015/01/21
PY  - 2015
N1  - https://doi.org/10.11648/j.ijmea.s.2015030103.16
DO  - 10.11648/j.ijmea.s.2015030103.16
T2  - International Journal of Mechanical Engineering and Applications
JF  - International Journal of Mechanical Engineering and Applications
JO  - International Journal of Mechanical Engineering and Applications
SP  - 35
EP  - 40
PB  - Science Publishing Group
SN  - 2330-0248
UR  - https://doi.org/10.11648/j.ijmea.s.2015030103.16
AB  - The purpose of this study is to calculate the geometries parameters for a wing NACA0012 as well as its materials in order to observe the instability of aeroelasticity such as divergence and flutter phenomenon in the low speed wind tunnel (38 m/s). Approaches used are the theories of aeroelasticity for the static and dynamic instability problem of the wing. The 3D divergence problem is solved first by strip theory to preliminary design the non-tapper wing and the suitable material for static instability at low speed. The V – g method for flutter analysis is carried out to verify the dynamic instability speed designed. A wing with wing chord, wing length is obtained in accordance with the testing section of the considered wind tunnel, and the suitable material is PU. The preliminary design were carried out for the the divergence phenomenon and divergence speeds can be observed at 30.34 m/s [10]. This study continues with the results based on dimensionless analysis of wing’s parameters on flutter speed.
VL  - 3
IS  - 1-3
ER  -

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Author Information

Thi Tuyet Nhung Le

Departement of Aerospace Engineering, Faculty of Transport Engineering, Ho Chi Minh City University of Technology, Ho Chi Minh city, Vietnam
Chi-Cong Nguyen

Departement of Aerospace Engineering, Faculty of Transport Engineering, Ho Chi Minh City University of Technology, Ho Chi Minh city, Vietnam
Hoang Nam Vang

Departement of Aerospace Engineering, Faculty of Transport Engineering, Ho Chi Minh City University of Technology, Ho Chi Minh city, Vietnam

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Plain Text BibTeX RIS

APA Style

Thi Tuyet Nhung Le, Chi-Cong Nguyen, Hoang Nam Vang. (2015). Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed. International Journal of Mechanical Engineering and Applications, 3(1-3), 35-40. https://doi.org/10.11648/j.ijmea.s.2015030103.16

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ACS Style

Thi Tuyet Nhung Le; Chi-Cong Nguyen; Hoang Nam Vang. Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed. Int. J. Mech. Eng. Appl. 2015, 3(1-3), 35-40. doi: 10.11648/j.ijmea.s.2015030103.16

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AMA Style

Thi Tuyet Nhung Le, Chi-Cong Nguyen, Hoang Nam Vang. Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed. Int J Mech Eng Appl. 2015;3(1-3):35-40. doi: 10.11648/j.ijmea.s.2015030103.16

Copy | Download

@article{10.11648/j.ijmea.s.2015030103.16,
  author = {Thi Tuyet Nhung Le and Chi-Cong Nguyen and Hoang Nam Vang},
  title = {Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed},
  journal = {International Journal of Mechanical Engineering and Applications},
  volume = {3},
  number = {1-3},
  pages = {35-40},
  doi = {10.11648/j.ijmea.s.2015030103.16},
  url = {https://doi.org/10.11648/j.ijmea.s.2015030103.16},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijmea.s.2015030103.16},
  abstract = {The purpose of this study is to calculate the geometries parameters for a wing NACA0012 as well as its materials in order to observe the instability of aeroelasticity such as divergence and flutter phenomenon in the low speed wind tunnel (38 m/s). Approaches used are the theories of aeroelasticity for the static and dynamic instability problem of the wing. The 3D divergence problem is solved first by strip theory to preliminary design the non-tapper wing and the suitable material for static instability at low speed. The V – g method for flutter analysis is carried out to verify the dynamic instability speed designed. A wing with wing chord, wing length is obtained in accordance with the testing section of the considered wind tunnel, and the suitable material is PU. The preliminary design were carried out for the the divergence phenomenon and divergence speeds can be observed at 30.34 m/s [10]. This study continues with the results based on dimensionless analysis of wing’s parameters on flutter speed.},
 year = {2015}
}

Copy | Download

TY  - JOUR
T1  - Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed
AU  - Thi Tuyet Nhung Le
AU  - Chi-Cong Nguyen
AU  - Hoang Nam Vang
Y1  - 2015/01/21
PY  - 2015
N1  - https://doi.org/10.11648/j.ijmea.s.2015030103.16
DO  - 10.11648/j.ijmea.s.2015030103.16
T2  - International Journal of Mechanical Engineering and Applications
JF  - International Journal of Mechanical Engineering and Applications
JO  - International Journal of Mechanical Engineering and Applications
SP  - 35
EP  - 40
PB  - Science Publishing Group
SN  - 2330-0248
UR  - https://doi.org/10.11648/j.ijmea.s.2015030103.16
AB  - The purpose of this study is to calculate the geometries parameters for a wing NACA0012 as well as its materials in order to observe the instability of aeroelasticity such as divergence and flutter phenomenon in the low speed wind tunnel (38 m/s). Approaches used are the theories of aeroelasticity for the static and dynamic instability problem of the wing. The 3D divergence problem is solved first by strip theory to preliminary design the non-tapper wing and the suitable material for static instability at low speed. The V – g method for flutter analysis is carried out to verify the dynamic instability speed designed. A wing with wing chord, wing length is obtained in accordance with the testing section of the considered wind tunnel, and the suitable material is PU. The preliminary design were carried out for the the divergence phenomenon and divergence speeds can be observed at 30.34 m/s [10]. This study continues with the results based on dimensionless analysis of wing’s parameters on flutter speed.
VL  - 3
IS  - 1-3
ER  -

Copy | Download