Numerical Simulation of the Vortex Shedding Behind an Airfoil-Spoiler Configuration
American Journal of Aerospace Engineering
Volume 5, Issue 1, June 2018, Pages: 16-23
Received: Jan. 16, 2018; Accepted: Jan. 31, 2018; Published: Feb. 28, 2018
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Amr Guaily, Engineering Mathematics and Physics Department, Cairo University, Giza, Egypt; Mechanical Engineering Department, Nile University, Giza, Egypt
Mohamed Abdelrahman, Aerospace Engineering Department, Cairo University, Giza, Egypt
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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.
Airfoil-Spoiler, Euler’s Equations, NACA 23012, Vortex Shedding, Boundary Conditions
To cite this article
Amr Guaily, Mohamed Abdelrahman, Numerical Simulation of the Vortex Shedding Behind an Airfoil-Spoiler Configuration, American Journal of Aerospace Engineering. Vol. 5, No. 1, 2018, pp. 16-23. doi: 10.11648/j.ajae.20180501.13
Copyright © 2018 Authors retain the copyright of this article.
This article is an open access article distributed under the Creative Commons Attribution License ( which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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