Open AccessNumerical Analysis of the Reynolds Number Effect on the Aerodynamic Performance Wing Airfoil Eppler 562 with Wingtip Fence
Author(s) -
Setyo Hariyadi,
S. Sutardi,
Wawan Aries Widodo,
Bambang Juni Pitoyo,
Nyaris Pambudiyatno,
Imam Sonhaji
Publication year - 2019
Publication title -
journal of physics. conference series
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.21
H-Index - 85
eISSN - 1742-6596
pISSN - 1742-6588
DOI - 10.1088/1742-6596/1381/1/012055
Subject(s) - wingtip device , airfoil , wing , angle of attack , aerodynamics , stall (fluid mechanics) , aerospace engineering , wing twist , lift coefficient , wing configuration , freestream , reynolds number , lift to drag ratio , turbulence , structural engineering , engineering , mechanics , physics
Wings are a very important part of aircraft. In that section, most of the lift forces are generated on the airplanes. The aerodynamic performance produced by the wing greatly determines how optimal the cruising range of an aircraft. To improve the performance of the wings, researchers have been competing to make wing modifications of an aircraft. One modification that is used at this time is by adding end wall which is often referred to as a winglet. Winglets function as a barrier to fluid flow jumps from the lower surface to the upper surface. This fluid flow jumps is often called as a tip vortex. One type of winglet discussed in this study is the wingtip fence. This study took wing objects on unmanned aerial vehicle with numerical simulation using Ansys 19.0 software with turbulent model k-ω SST. The freestream flow rate to be used are 10 m/s ( Re = 2,34 x 10 4 ) and 45 m/s ( Re = 1 x 10 5 ). The angle of attack used are ( α ) = 0°, 2°, 4°, 6°, 8°, 10°,12°,15°, 17°, and 19°. The wing model is an Eppler 562 (E562) airfoil with and without a winglet. From this study, it was found that wing aerodynamic performance with Eppler 562 (E562) airfoil was higher at Re = 2,34 x 10 4 Delay of the stall is more effective at Re = 1 x 10 5 compared to the Re = 2,34 x 10 4 But, the aerodynamic performance Re = 2,34 x 10 4 better than Re = 1 x 10 5 .