Aeroelastic Simulation of Stall Flutter Undergoing High ‎and Low Amplitude Limit Cycle Oscillations

The aeroelastic behaviour of an airfoil oscillating in large and small pitch amplitudes due to nonlinearity ‎in aerodynamics is examined. The phenomenon of stall flutter resulted in the limit cycle oscillations of ‎NACA 0012 at low to intermediate Reynolds number is investigated numerically through...

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Autores principales:	M. K. H. M. Zorkipli, A. Abbas, N. A. Razak
Formato:	article
Lenguaje:	EN
Publicado:	Isfahan University of Technology 2021
Materias:	stall flutter; limit cycle oscillation; flow separation. Mechanical engineering and machinery TJ1-1570
Acceso en línea:	https://doaj.org/article/da2abd98485a40b185207da87a7ad7fd
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spelling	oai:doaj.org-article:da2abd98485a40b185207da87a7ad7fd2021-11-13T07:03:04ZAeroelastic Simulation of Stall Flutter Undergoing High ‎and Low Amplitude Limit Cycle Oscillations1735-3572https://doaj.org/article/da2abd98485a40b185207da87a7ad7fd2021-01-01T00:00:00Zhttp://jafmonline.net/JournalArchive/download?file_ID=56911&issue_ID=1015https://doaj.org/toc/1735-3572The aeroelastic behaviour of an airfoil oscillating in large and small pitch amplitudes due to nonlinearity ‎in aerodynamics is examined. The phenomenon of stall flutter resulted in the limit cycle oscillations of ‎NACA 0012 at low to intermediate Reynolds number is investigated numerically through the unsteady ‎two-dimensional aeroelastic simulation. The simulations employed unsteady Reynolds Average Navier ‎Stokes shear stress transport k-ω turbulent model with the low Reynolds number correction. The ‎simulations of the fluid-structure interaction were performed by coupling the structural equation of ‎motion with a fluid solver through the user-defined function utility. Numerical simulations were executed ‎at three different elastic axis positions; the leading-edge, 18% and 36% of the airfoil chord length. The ‎airfoil chord measures 0.156 m. The simulations were executed at the free stream velocity ranging from ‎‎5.0 m/s to 13 m/s corresponding to the Reynolds number between 51618 and 134207. Two types of ‎oscillation amplitudes were observed at each elastic axis position. At the leading-edge and 18% case, ‎small amplitude oscillations were observed while at 36%, the system underwent high amplitude ‎oscillations. The analysis revealed the cause for small oscillation amplitude is due to the separation of the ‎laminar boundary layer on the suction side of the airfoil starting at the trailing edge. High amplitude ‎oscillations occurred due to the existence of the dynamic stall phenomenon beginning at the leading-edge. ‎Small amplitude LCOs only occurred within a limited range of airspeed before it disappeared due to ‎increasing airspeed‎‎.M. K. H. M. ZorkipliA. AbbasN. A. RazakIsfahan University of Technology articlestall flutter; limit cycle oscillation; flow separation.Mechanical engineering and machineryTJ1-1570ENJournal of Applied Fluid Mechanics, Vol 14, Iss 6, Pp 1679-1689 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	stall flutter; limit cycle oscillation; flow separation. Mechanical engineering and machinery TJ1-1570
spellingShingle	stall flutter; limit cycle oscillation; flow separation. Mechanical engineering and machinery TJ1-1570 M. K. H. M. Zorkipli A. Abbas N. A. Razak Aeroelastic Simulation of Stall Flutter Undergoing High ‎and Low Amplitude Limit Cycle Oscillations
description	The aeroelastic behaviour of an airfoil oscillating in large and small pitch amplitudes due to nonlinearity ‎in aerodynamics is examined. The phenomenon of stall flutter resulted in the limit cycle oscillations of ‎NACA 0012 at low to intermediate Reynolds number is investigated numerically through the unsteady ‎two-dimensional aeroelastic simulation. The simulations employed unsteady Reynolds Average Navier ‎Stokes shear stress transport k-ω turbulent model with the low Reynolds number correction. The ‎simulations of the fluid-structure interaction were performed by coupling the structural equation of ‎motion with a fluid solver through the user-defined function utility. Numerical simulations were executed ‎at three different elastic axis positions; the leading-edge, 18% and 36% of the airfoil chord length. The ‎airfoil chord measures 0.156 m. The simulations were executed at the free stream velocity ranging from ‎‎5.0 m/s to 13 m/s corresponding to the Reynolds number between 51618 and 134207. Two types of ‎oscillation amplitudes were observed at each elastic axis position. At the leading-edge and 18% case, ‎small amplitude oscillations were observed while at 36%, the system underwent high amplitude ‎oscillations. The analysis revealed the cause for small oscillation amplitude is due to the separation of the ‎laminar boundary layer on the suction side of the airfoil starting at the trailing edge. High amplitude ‎oscillations occurred due to the existence of the dynamic stall phenomenon beginning at the leading-edge. ‎Small amplitude LCOs only occurred within a limited range of airspeed before it disappeared due to ‎increasing airspeed‎‎.
format	article
author	M. K. H. M. Zorkipli A. Abbas N. A. Razak
author_facet	M. K. H. M. Zorkipli A. Abbas N. A. Razak
author_sort	M. K. H. M. Zorkipli
title	Aeroelastic Simulation of Stall Flutter Undergoing High ‎and Low Amplitude Limit Cycle Oscillations
title_short	Aeroelastic Simulation of Stall Flutter Undergoing High ‎and Low Amplitude Limit Cycle Oscillations
title_full	Aeroelastic Simulation of Stall Flutter Undergoing High ‎and Low Amplitude Limit Cycle Oscillations
title_fullStr	Aeroelastic Simulation of Stall Flutter Undergoing High ‎and Low Amplitude Limit Cycle Oscillations
title_full_unstemmed	Aeroelastic Simulation of Stall Flutter Undergoing High ‎and Low Amplitude Limit Cycle Oscillations
title_sort	aeroelastic simulation of stall flutter undergoing high ‎and low amplitude limit cycle oscillations
publisher	Isfahan University of Technology
publishDate	2021
url	https://doaj.org/article/da2abd98485a40b185207da87a7ad7fd
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Aeroelastic Simulation of Stall Flutter Undergoing High ‎and Low Amplitude Limit Cycle Oscillations

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