Effect of the trailing edge geometry on the unsteadiness of the flow around a stalled NACA 0015 airfoil

Wei He, Francisco Jose Gomez Carrasco, Daniel Rodriguez, Vassilis Theofilis

Research output: Chapter in Book/Report/Conference proceedingChapter (Book)Researchpeer-review

2 Citations (Scopus)

Abstract

The effect on the flow unsteadiness on a NACA 0015 airfoil at Reynolds number Re = 200 and Angle of Attack AoA = 18 degrees is investigated numerically. Four different geometries based on the NACA 0015 airfoil and with trailing-edge modifications are compared. Long-time integration of the incompressible two-dimensional Navier-Stokes equations shows that the recovered flow field is steady independently of the trailing-edge geometry
Original languageEnglish
Title of host publicationInstability and Control of Massively Separated Flows: Proceedings of the International Conference on Instability and Control of Massively Separated Flows, held in Prato, Italy, from 4-6 September 2013
EditorsVassilis Theofilis, Julio Soria
Place of PublicationCham Switzerland
PublisherSpringer
Pages45 - 50
Number of pages6
Edition1
ISBN (Print)9783319062594
DOIs
Publication statusPublished - 2015

Publication series

NameFluid Mechanics and Its Applications
PublisherSpringer
Volume107

Cite this

He, W., Gomez Carrasco, F. J., Rodriguez, D., & Theofilis, V. (2015). Effect of the trailing edge geometry on the unsteadiness of the flow around a stalled NACA 0015 airfoil. In V. Theofilis, & J. Soria (Eds.), Instability and Control of Massively Separated Flows: Proceedings of the International Conference on Instability and Control of Massively Separated Flows, held in Prato, Italy, from 4-6 September 2013 (1 ed., pp. 45 - 50). (Fluid Mechanics and Its Applications; Vol. 107). Cham Switzerland: Springer. https://doi.org/10.1007/978-3-319-06260-0_6
He, Wei ; Gomez Carrasco, Francisco Jose ; Rodriguez, Daniel ; Theofilis, Vassilis. / Effect of the trailing edge geometry on the unsteadiness of the flow around a stalled NACA 0015 airfoil. Instability and Control of Massively Separated Flows: Proceedings of the International Conference on Instability and Control of Massively Separated Flows, held in Prato, Italy, from 4-6 September 2013. editor / Vassilis Theofilis ; Julio Soria. 1. ed. Cham Switzerland : Springer, 2015. pp. 45 - 50 (Fluid Mechanics and Its Applications).
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abstract = "The effect on the flow unsteadiness on a NACA 0015 airfoil at Reynolds number Re = 200 and Angle of Attack AoA = 18 degrees is investigated numerically. Four different geometries based on the NACA 0015 airfoil and with trailing-edge modifications are compared. Long-time integration of the incompressible two-dimensional Navier-Stokes equations shows that the recovered flow field is steady independently of the trailing-edge geometry",
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He, W, Gomez Carrasco, FJ, Rodriguez, D & Theofilis, V 2015, Effect of the trailing edge geometry on the unsteadiness of the flow around a stalled NACA 0015 airfoil. in V Theofilis & J Soria (eds), Instability and Control of Massively Separated Flows: Proceedings of the International Conference on Instability and Control of Massively Separated Flows, held in Prato, Italy, from 4-6 September 2013. 1 edn, Fluid Mechanics and Its Applications, vol. 107, Springer, Cham Switzerland, pp. 45 - 50. https://doi.org/10.1007/978-3-319-06260-0_6

Effect of the trailing edge geometry on the unsteadiness of the flow around a stalled NACA 0015 airfoil. / He, Wei; Gomez Carrasco, Francisco Jose; Rodriguez, Daniel; Theofilis, Vassilis.

Instability and Control of Massively Separated Flows: Proceedings of the International Conference on Instability and Control of Massively Separated Flows, held in Prato, Italy, from 4-6 September 2013. ed. / Vassilis Theofilis; Julio Soria. 1. ed. Cham Switzerland : Springer, 2015. p. 45 - 50 (Fluid Mechanics and Its Applications; Vol. 107).

Research output: Chapter in Book/Report/Conference proceedingChapter (Book)Researchpeer-review

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AB - The effect on the flow unsteadiness on a NACA 0015 airfoil at Reynolds number Re = 200 and Angle of Attack AoA = 18 degrees is investigated numerically. Four different geometries based on the NACA 0015 airfoil and with trailing-edge modifications are compared. Long-time integration of the incompressible two-dimensional Navier-Stokes equations shows that the recovered flow field is steady independently of the trailing-edge geometry

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He W, Gomez Carrasco FJ, Rodriguez D, Theofilis V. Effect of the trailing edge geometry on the unsteadiness of the flow around a stalled NACA 0015 airfoil. In Theofilis V, Soria J, editors, Instability and Control of Massively Separated Flows: Proceedings of the International Conference on Instability and Control of Massively Separated Flows, held in Prato, Italy, from 4-6 September 2013. 1 ed. Cham Switzerland: Springer. 2015. p. 45 - 50. (Fluid Mechanics and Its Applications). https://doi.org/10.1007/978-3-319-06260-0_6