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

Amr Guaily; Mohamed Abdelrahman

doi:doi:10.11648/j.ajae.20180501.13

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

Amr Guaily, Mohamed Abdelrahman

Published in American Journal of Aerospace Engineering (Volume 5, Issue 1)

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

[1]	Pfeiffer, J. & Zumwalt, G. W. (1982). Computation Model for Low Speed Flows Past Airfoils with Spoilers. AIAA Journal, 20 (3), 376-382.
[2]	Wentz, Jr. & Ostowari, C. (1981). Effects of Design Variables on Spoiler Control Effectiveness, Hing Moments and Wake. The Proceedings of the AIAA 1981-0072.
[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.
[4]	Mack, D., Seetharam, C., Kuhn, G., & Bright, T. (1979). Aerodynamics spoiler Control Devices, Proceeding of the AIAA Conference. Paper 79-1873.
[5]	Lee, S., Bodapati, S. (1987). Experimental Investigation of the flow field of an airfoil with spoiler. AIAA Journal 25 (11), 1411-1416.
[6]	Choi, W., Chang, S., Ok, H. (2001). Parametric Study of a deploying Spoiler with two-Equation Turbulence Model. Proceeding of the AIAA Paper 2001-0864.
[7]	Gand, F. (2013). Zonal Detached Eddy Simulation of a Civil Aircraft with a Deflected Spoiler. AIAA Journal, 51 (3), 697-706.
[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.
[9]	Wang, W., Liu, P. (2017). Numerical study of the influence of spoiler deflection on high-lift configuration. Theoretical and Applied Mechanics Letters, 7 (3), 159-163.
[10]	Geisbauer, S., Loser, T. (2017). Towards the Investigation of Unsteady Spoiler Aerodynamics. Proceeding of the 35th AIAA Applied Aerodynamics Conference AIAA Paper 2017-4229.
[11]	Lynn, P., & Arya, K. (1973). Use of the least squares criterion in the finite element formulation. International Journal for Numerical Methods in Engineering, 6, 75-88.
[12]	Taghaddosi, F., Habashi, G., Guevremont, G., & Ait-Ali-Yahia, D. (1999). An Adaptive Least-Squares Method for the Compressible Euler Equations. International Journal for Numerical Methods in Fluids, 31, 1121-1139.
[13]	Brooks, A., Hughes, R. (1982). Streamline upwind/Petrov–Galerkin formulations for convection dominated flows with particular emphasis on the incompressible Navier–Stokes equations. Computer Methods in Applied Mechanics and Engineering, 32, 199–259.
[14]	Hughes, R., Franca, P., & Hulbert, M. (1989). A new finite element formulation for computational fluid dynamics: VIII. The Galerkin/Least-squares method for advctive-diffusive equations, Computer Methods in Applied Mechanics and Engineering, 73, 173-189.
[15]	Brezzi, F., Bristeau, M., Franca, L., Mallet, M., & Roge´, G. (1992). A relationship between stabilized finite element methods and the Galerkin method with bubble functions. Computer Methods in Applied Mechanics and Engineering, 96, 117–129.
[16]	Baiocchi, C., Brezzi, F., Franca, L. (1993). Virtual bubbles and the Galerkin-least-squares method, Computer Methods in Applied Mechanics and Engineering, 105, 125–141.
[17]	Brezzi, F. & Russo, A. (1994). Choosing bubbles for advection–diffusion problems. Mathematical Models and Methods in Applied Sciences, 4, 571–587.
[18]	Franca, P., & Russo, A. (1996). Deriving upwinding, mass lumping and selective reduced integration by residual-free bubbles. Applied Mathematics Letters, 9, 83–88.
[19]	Guermond, L., (1999). Stabilization par viscosite´ de sous-maille pour l_approximation de Galerkin des ope`rateurs monotones. C. R. Acad. Sci., Paris, Se´rie Rouge I, 328, 617–622.
[20]	Russo, A. (2006). Streamline-upwind Petrov/Galerkin method (SUPG) vs residual-free bubbles (RFB), Computer Methods in Applied Mechanics and Engineering, 195, 1608–1620.
[21]	Hughes, R., (1995). Multiscale phenomena: Green’s functions, the Dirichlet-to-Neumann formulation, subgrid scale models, bubbles and the origin of stabilized methods. Computer Methods in Applied Mechanics and Engineering, 127, 387–401.
[22]	Brezzi, F., Franca, P., Hughes, R., Russo, A. (1997). b= integral of g. Computer Methods in Applied Mechanics and Engineering, 145, 329–339.
[23]	Guaily, A., & Megahed, A. (2010). An adaptive finite element method for planar and axisymmetric compressible flows. Finite Elements in Analysis Design, 46, 613–624.
[24]	Guaily, A., & Epstein, M. (2010). A unified hyperbolic model for viscoelastic liquids. Mechanics Research Communications, 37, 158–163.
[25]	Guaily, A., & Epstein, M. (2013). Boundary Conditions for hyperbolic System of partial differentials equation. Journal of advanced research, 4, 321-329.
[26]	Bartecki, K. (2016). Modeling and Analysis of Linear Hyperbolic Systems of Balance Laws. Springer International Publishing Press.
[27]	Reddy, N. (1993) An Introduction to the Finite Element Method. McGraw-Hill, New York.
[28]	Moussaoui, F. (2003). A Unified Approach for Inviscid Compressible and Nearly Incompressible Flow by Least-Squares Finite Element Method. Applied Numerical Mathematics, 44, 183-199.

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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
Y1  - 2018/02/28
PY  - 2018
N1  - https://doi.org/10.11648/j.ajae.20180501.13
DO  - 10.11648/j.ajae.20180501.13
T2  - American Journal of Aerospace Engineering
JF  - American Journal of Aerospace Engineering
JO  - American Journal of Aerospace Engineering
SP  - 16
EP  - 23
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

Amr Guaily

Engineering Mathematics and Physics Department, Cairo University, Giza, Egypt
Mohamed Abdelrahman

Aerospace Engineering Department, Cairo University, Giza, Egypt

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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

Copy | Download

@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}
}

Copy | Download

TY  - JOUR
T1  - Numerical Simulation of the Vortex Shedding Behind an Airfoil-Spoiler Configuration
AU  - Amr Guaily
AU  - Mohamed Abdelrahman
Y1  - 2018/02/28
PY  - 2018
N1  - https://doi.org/10.11648/j.ajae.20180501.13
DO  - 10.11648/j.ajae.20180501.13
T2  - American Journal of Aerospace Engineering
JF  - American Journal of Aerospace Engineering
JO  - American Journal of Aerospace Engineering
SP  - 16
EP  - 23
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  -

Copy | Download