Proceedings of the International Conference on Advance Transportation, Engineering, and Applied Science (ICATEAS 2022)

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Numerical Simulation of Rectangular Vortex Generator in Sweptback Wing Airfoil NACA 0012 with Counter-Rotating Position

Authors
Verdhiana Sembodo Putra1, *, Setyo Hariyadi Suranto Putro1, Nyaris Pambudiyatno1
1Politeknik Penerbangan Surabaya, Jemur Andayani I/73 Wonocolo, Surabaya, 60236, Jawa Timur, Indonesia
*Corresponding author. Email: verdhiputra25@gmail.com
Corresponding Author
Verdhiana Sembodo Putra
Available Online 21 February 2023.
DOI
10.2991/978-94-6463-092-3_23How to use a DOI?
Keywords
vortex generator; airfoil; aerodynamic; NACA 0012
Abstract

Airplanes can fly because of the slightly curved shape of the plane’s wings called the airfoil. Airfoil is still used by aircraft today but continues to be designed to get maximum results. The research method used is a simulation analysis method on the NACA 0012 test object with ANSYS-CFD software which is given a variation in the shape of a rectangle vortex generator with a length of 15 mm, a width of 10 mm, and a distance between vortex generators of 10 cm. The angles of attack reviewed are 0°, 2°, 4°, 6°, 8°, 10°, 12°, 14°, 15°, 16°, 18°, and 20°. The result of this simulation is that the presence of a rectangular vortex generator on airfoil NACA 0012 can affect both performance and aerodynamic characteristics. The vortex generator on the airfoil can delay the occurrence of separation and can delay the occurrence of stall on the NACA 0012 airfoil, where the ordinary NACA 0012 airfoil stalls at α = 14° with the addition of the vortex generator has not stalled at this point. With this, the NACA 0012 airfoil which is given a vortex generator can affect the results of CD. Overall, the most optimal variation is the NACA 0012 airfoil which is given a vortex generator with x/c = 15% where the value of CD is greatest at an angle of attack α = 18°.

Copyright
© 2023 The Author(s)
Open Access
Open Access This chapter is licensed under the terms of the Creative Commons Attribution-NonCommercial 4.0 International License (http://creativecommons.org/licenses/by-nc/4.0/), which permits any noncommercial use, sharing, adaptation, distribution and reproduction in any medium or format, as long as you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons license and indicate if changes were made.

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Volume Title
Proceedings of the International Conference on Advance Transportation, Engineering, and Applied Science (ICATEAS 2022)
Series
Advances in Engineering Research
Publication Date
21 February 2023
ISBN
10.2991/978-94-6463-092-3_23
ISSN
2352-5401
DOI
10.2991/978-94-6463-092-3_23How to use a DOI?
Copyright
© 2023 The Author(s)
Open Access
Open Access This chapter is licensed under the terms of the Creative Commons Attribution-NonCommercial 4.0 International License (http://creativecommons.org/licenses/by-nc/4.0/), which permits any noncommercial use, sharing, adaptation, distribution and reproduction in any medium or format, as long as you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons license and indicate if changes were made.

Cite this article

risenwbib
TY  - CONF
AU  - Verdhiana Sembodo Putra
AU  - Setyo Hariyadi Suranto Putro
AU  - Nyaris Pambudiyatno
PY  - 2023
DA  - 2023/02/21
TI  - Numerical Simulation of Rectangular Vortex Generator in Sweptback Wing Airfoil NACA 0012 with Counter-Rotating Position
BT  - Proceedings of the International Conference on Advance Transportation, Engineering, and Applied Science (ICATEAS 2022)
PB  - Atlantis Press
SP  - 263
EP  - 275
SN  - 2352-5401
UR  - https://doi.org/10.2991/978-94-6463-092-3_23
DO  - 10.2991/978-94-6463-092-3_23
ID  - Putra2023
ER  -