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Numerical Simulation of the Vortex Shedding Behind an Airfoil-Spoiler Configuration

Received: 16 January 2018     Accepted: 31 January 2018     Published: 28 February 2018
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Abstract

Spoilers are widely used on aircrafts as lateral control devices. Despite their wide usage, very little numerical and theoretical information exist. Numerical simulation of the full unsteady, compressible Euler’s equations over the NACA 23012 airfoil with spoiler is performed using a hybrid Least-Squares finite element/finite difference method coupled to the Newton-Raphson’s linearization technique. The flow patterns behind the spoiler are presented. The pressure coefficient over the upper and lower surfaces are successfully compared to previously published experimental work. The vortex shedding due to the existence of the spoiler is strong specially at high deflection angles. Convection of the vortices will affect the performance of the tail and so a future study of the wing-tail interaction is needed.

Published in American Journal of Aerospace Engineering (Volume 5, Issue 1)
DOI 10.11648/j.ajae.20180501.13
Page(s) 16-23
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), 2018. Published by Science Publishing Group

Keywords

Airfoil-Spoiler, Euler’s Equations, NACA 23012, Vortex Shedding, Boundary Conditions

References
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[3] Abdelrahman, M. (1993). Numerical and Experimental Investigations of the Flow Field Past Airfoil-Spoiler Configuration. In the Proceedings of the First Pacific International Conference on Aerospace Science and technology 1993, PICAST’I, Tainan, Taiwan, Rep. of China.
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[8] Alhawwary, A., Owis, M., Abdelrahman, M. (2015). Numerical Simulation of the Flow field around Airfoil with Spoiler using the Higher Order Spectral Difference Method. Proceeding of the AIAA conference. Paper 2015-1499.
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Cite This Article
  • APA Style

    Amr Guaily, Mohamed Abdelrahman. (2018). Numerical Simulation of the Vortex Shedding Behind an Airfoil-Spoiler Configuration. American Journal of Aerospace Engineering, 5(1), 16-23. https://doi.org/10.11648/j.ajae.20180501.13

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    ACS Style

    Amr Guaily; Mohamed Abdelrahman. Numerical Simulation of the Vortex Shedding Behind an Airfoil-Spoiler Configuration. Am. J. Aerosp. Eng. 2018, 5(1), 16-23. doi: 10.11648/j.ajae.20180501.13

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    AMA Style

    Amr Guaily, Mohamed Abdelrahman. Numerical Simulation of the Vortex Shedding Behind an Airfoil-Spoiler Configuration. Am J Aerosp Eng. 2018;5(1):16-23. doi: 10.11648/j.ajae.20180501.13

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  • @article{10.11648/j.ajae.20180501.13,
      author = {Amr Guaily and Mohamed Abdelrahman},
      title = {Numerical Simulation of the Vortex Shedding Behind an Airfoil-Spoiler Configuration},
      journal = {American Journal of Aerospace Engineering},
      volume = {5},
      number = {1},
      pages = {16-23},
      doi = {10.11648/j.ajae.20180501.13},
      url = {https://doi.org/10.11648/j.ajae.20180501.13},
      eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.20180501.13},
      abstract = {Spoilers are widely used on aircrafts as lateral control devices. Despite their wide usage, very little numerical and theoretical information exist. Numerical simulation of the full unsteady, compressible Euler’s equations over the NACA 23012 airfoil with spoiler is performed using a hybrid Least-Squares finite element/finite difference method coupled to the Newton-Raphson’s linearization technique. The flow patterns behind the spoiler are presented. The pressure coefficient over the upper and lower surfaces are successfully compared to previously published experimental work. The vortex shedding due to the existence of the spoiler is strong specially at high deflection angles. Convection of the vortices will affect the performance of the tail and so a future study of the wing-tail interaction is needed.},
     year = {2018}
    }
    

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  • TY  - JOUR
    T1  - Numerical Simulation of the Vortex Shedding Behind an Airfoil-Spoiler Configuration
    AU  - Amr Guaily
    AU  - Mohamed Abdelrahman
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    T2  - American Journal of Aerospace Engineering
    JF  - American Journal of Aerospace Engineering
    JO  - American Journal of Aerospace Engineering
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    PB  - Science Publishing Group
    SN  - 2376-4821
    UR  - https://doi.org/10.11648/j.ajae.20180501.13
    AB  - Spoilers are widely used on aircrafts as lateral control devices. Despite their wide usage, very little numerical and theoretical information exist. Numerical simulation of the full unsteady, compressible Euler’s equations over the NACA 23012 airfoil with spoiler is performed using a hybrid Least-Squares finite element/finite difference method coupled to the Newton-Raphson’s linearization technique. The flow patterns behind the spoiler are presented. The pressure coefficient over the upper and lower surfaces are successfully compared to previously published experimental work. The vortex shedding due to the existence of the spoiler is strong specially at high deflection angles. Convection of the vortices will affect the performance of the tail and so a future study of the wing-tail interaction is needed.
    VL  - 5
    IS  - 1
    ER  - 

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Author Information
  • Engineering Mathematics and Physics Department, Cairo University, Giza, Egypt

  • Aerospace Engineering Department, Cairo University, Giza, Egypt

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