Aerodynamic Study of a NACA 64418 Rectangular Wing under Forced Pitching Motions

The aerodynamic behavior of a pitching NACA 64418 rectangular wing was experimentally studied in a subsonic wind tunnel. The wing had a chord c = 0.5 m, a span which covered the distance between the two parallel tunnel walls and an axis of rotation 0.35 c far from the leading edge. Based on pressure...

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Autores principales:	Dimitris Gkiolas, Dimitrios Mathioulakis
Formato:	article
Lenguaje:	EN
Publicado:	MDPI AG 2021
Materias:	pitching double stall aerodynamic damping dynamic stall NACA 64418 Thermodynamics QC310.15-319 Descriptive and experimental mechanics QC120-168.85
Acceso en línea:	https://doaj.org/article/81d278c7bdf347dea293b89b1e84378e
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spelling	oai:doaj.org-article:81d278c7bdf347dea293b89b1e84378e2021-11-25T17:31:37ZAerodynamic Study of a NACA 64418 Rectangular Wing under Forced Pitching Motions10.3390/fluids61103942311-5521https://doaj.org/article/81d278c7bdf347dea293b89b1e84378e2021-11-01T00:00:00Zhttps://www.mdpi.com/2311-5521/6/11/394https://doaj.org/toc/2311-5521The aerodynamic behavior of a pitching NACA 64418 rectangular wing was experimentally studied in a subsonic wind tunnel. The wing had a chord c = 0.5 m, a span which covered the distance between the two parallel tunnel walls and an axis of rotation 0.35 c far from the leading edge. Based on pressure distribution and flow visualization, intermittent flow separation (double stall) was revealed near the leading edge suction side when the wing was stationary, at angles higher than 17° and Re = 0.5 × 10<sup>6</sup>. Under pitching oscillations, aerodynamic loads were calculated by integrating the output data of fast responding surface pressure transducers for various mean angles of attack (α<sub>m (max)</sub> = 15°), reduced frequencies (k<sub>max</sub> = 0.2) and angle amplitudes Δα in the interval [2°, 8°]. The impact of the above parameters up to Re = 0.75 × 10<sup>6</sup> on the cycle-averaged lift and pitching moment loops is discussed and the cycle aerodynamic damping coefficient is calculated. Moreover, the boundaries of the above parameters are defined for the case that energy is transferred from the flow to the wing (negative aerodynamic damping coefficient), indicating the conditions under which aeroelastic instabilities are probable to occur.Dimitris GkiolasDimitrios MathioulakisMDPI AGarticlepitchingdouble stallaerodynamic dampingdynamic stallNACA 64418ThermodynamicsQC310.15-319Descriptive and experimental mechanicsQC120-168.85ENFluids, Vol 6, Iss 394, p 394 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	pitching double stall aerodynamic damping dynamic stall NACA 64418 Thermodynamics QC310.15-319 Descriptive and experimental mechanics QC120-168.85
spellingShingle	pitching double stall aerodynamic damping dynamic stall NACA 64418 Thermodynamics QC310.15-319 Descriptive and experimental mechanics QC120-168.85 Dimitris Gkiolas Dimitrios Mathioulakis Aerodynamic Study of a NACA 64418 Rectangular Wing under Forced Pitching Motions
description	The aerodynamic behavior of a pitching NACA 64418 rectangular wing was experimentally studied in a subsonic wind tunnel. The wing had a chord c = 0.5 m, a span which covered the distance between the two parallel tunnel walls and an axis of rotation 0.35 c far from the leading edge. Based on pressure distribution and flow visualization, intermittent flow separation (double stall) was revealed near the leading edge suction side when the wing was stationary, at angles higher than 17° and Re = 0.5 × 10<sup>6</sup>. Under pitching oscillations, aerodynamic loads were calculated by integrating the output data of fast responding surface pressure transducers for various mean angles of attack (α<sub>m (max)</sub> = 15°), reduced frequencies (k<sub>max</sub> = 0.2) and angle amplitudes Δα in the interval [2°, 8°]. The impact of the above parameters up to Re = 0.75 × 10<sup>6</sup> on the cycle-averaged lift and pitching moment loops is discussed and the cycle aerodynamic damping coefficient is calculated. Moreover, the boundaries of the above parameters are defined for the case that energy is transferred from the flow to the wing (negative aerodynamic damping coefficient), indicating the conditions under which aeroelastic instabilities are probable to occur.
format	article
author	Dimitris Gkiolas Dimitrios Mathioulakis
author_facet	Dimitris Gkiolas Dimitrios Mathioulakis
author_sort	Dimitris Gkiolas
title	Aerodynamic Study of a NACA 64418 Rectangular Wing under Forced Pitching Motions
title_short	Aerodynamic Study of a NACA 64418 Rectangular Wing under Forced Pitching Motions
title_full	Aerodynamic Study of a NACA 64418 Rectangular Wing under Forced Pitching Motions
title_fullStr	Aerodynamic Study of a NACA 64418 Rectangular Wing under Forced Pitching Motions
title_full_unstemmed	Aerodynamic Study of a NACA 64418 Rectangular Wing under Forced Pitching Motions
title_sort	aerodynamic study of a naca 64418 rectangular wing under forced pitching motions
publisher	MDPI AG
publishDate	2021
url	https://doaj.org/article/81d278c7bdf347dea293b89b1e84378e
work_keys_str_mv	AT dimitrisgkiolas aerodynamicstudyofanaca64418rectangularwingunderforcedpitchingmotions AT dimitriosmathioulakis aerodynamicstudyofanaca64418rectangularwingunderforcedpitchingmotions
_version_	1718412234411999232

Aerodynamic Study of a NACA 64418 Rectangular Wing under Forced Pitching Motions

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