Numerical study of flow characteristics around wing airfoil Eppler 562 with variations of rearward wingtip fence

S. P. Setyo Hariyadi*, Sutardi, Wawan Aries Widodo

*Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

5 Citations (Scopus)


To produce lift on the wing of the aircraft, pressure distribution on the upper surface of the wing must be lower than the pressure on the lower of the wing. This can be done by making the air passage on the upper surface is longer than that on the bottom surface, or making the wing's relative angle to the direction of the incoming stream of air. Air will tend to flow from areas with high pressure to areas with low pressure. The pressure difference between lower surface of the wing higher than the top surface of the wing also results in the occurrence of this airflow. The place that allows for the occurrence of "leakage" of this air is at the tip of the wing. The flow from lower surface to the upper upper surface of the wings produces a vortex flow similar to a small tornado known as wingtip vortices. This whirl causes the air tend to flow downward on the wing area, and referred to as the term downwash. One modification on the aircraft wing to reduce the impact of the vortex tip is the use of the winglet on the tip of the aircraft wing. This has been widely applied to the latest commercial aircraft to improve the efficiency of the aircraft. The numerical study was done using CFD software with 3D geometry configuration. The geometry of the specimen is airplane wing Eppler 562 with chord length of 0.036 m, swept angle 0°and modification of winglet type rearward wingtip fence winglet with cant angle of 75°. The airflow with velocity at the inlet of 10 m/s. The turbulent modeling is k-ω SST. Present study uses hybrid mesh with boundary layer mesh method. From the simulation results it is shown that there is an increase in lift coefficient (CL) and an increase in drag coefficient (CD) along with the increase of angle of attack. In rearward wingtip fence with cant angle 0°produce CL/CD better than cant angle 75°and plain wing. Rearward wingtip fence shows optimum performance of α = 8°settings compared to plain wing.

Original languageEnglish
Title of host publicationDisruptive Innovation in Mechanical Engineering for Industry Competitiveness
Subtitle of host publicationProceedings of the 3rd International Conference on Mechanical Engineering, ICOME 2017
EditorsVivien S. Djanali, Suwarno, Bambang Pramujati, Volodymyr A. Yartys
PublisherAmerican Institute of Physics Inc.
ISBN (Electronic)9780735416994
Publication statusPublished - 13 Jul 2018
Event3rd International Conference on Mechanical Engineering, ICOME 2017 - Surabaya, Indonesia
Duration: 5 Oct 20176 Oct 2017

Publication series

NameAIP Conference Proceedings
ISSN (Print)0094-243X
ISSN (Electronic)1551-7616


Conference3rd International Conference on Mechanical Engineering, ICOME 2017


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